NYU/GRUMMAN K-1 AIRFOIL (k1-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NYU/GRUMMAN K-1 AIRFOIL (k1-il) Reynolds number: 1,000,000 Max Cl/Cd: 80.67 at α=1.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k1-il-1000000.txt Download as CSV file: xf-k1-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NYU/GRUMMAN K-1 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.9911 0.11130 0.10901 -0.0137 1.0000 0.0150
-17.000 -1.0388 0.09733 0.09480 -0.0221 1.0000 0.0149
-16.750 -1.0651 0.08818 0.08548 -0.0276 1.0000 0.0149
-16.500 -1.0839 0.08066 0.07782 -0.0323 1.0000 0.0149
-16.250 -1.0990 0.07408 0.07110 -0.0365 1.0000 0.0150
-16.000 -1.1101 0.06836 0.06526 -0.0400 1.0000 0.0151
-15.750 -1.1195 0.06314 0.05991 -0.0433 1.0000 0.0152
-15.500 -1.1270 0.05847 0.05512 -0.0461 1.0000 0.0153
-15.250 -1.1328 0.05427 0.05081 -0.0486 1.0000 0.0154
-15.000 -1.1367 0.05043 0.04685 -0.0508 1.0000 0.0155
-14.750 -1.1387 0.04696 0.04325 -0.0527 1.0000 0.0156
-14.500 -1.1386 0.04379 0.03996 -0.0545 1.0000 0.0158
-14.250 -1.1364 0.04093 0.03699 -0.0560 1.0000 0.0159
-14.000 -1.1317 0.03841 0.03434 -0.0575 1.0000 0.0161
-13.750 -1.1244 0.03620 0.03202 -0.0590 1.0000 0.0163
-13.500 -1.1148 0.03428 0.02998 -0.0605 1.0000 0.0164
-13.250 -1.1117 0.03152 0.02709 -0.0611 1.0000 0.0167
-13.000 -1.1006 0.02969 0.02522 -0.0619 1.0000 0.0170
-12.750 -1.0858 0.02824 0.02375 -0.0630 1.0000 0.0173
-12.500 -1.0703 0.02692 0.02238 -0.0642 1.0000 0.0175
-12.250 -1.0521 0.02559 0.02097 -0.0658 0.9980 0.0178
-12.000 -1.0245 0.02425 0.01954 -0.0688 0.9927 0.0181
-11.750 -0.9986 0.02310 0.01831 -0.0707 0.9878 0.0184
-11.500 -0.9734 0.02210 0.01722 -0.0720 0.9831 0.0187
-11.250 -0.9488 0.02124 0.01626 -0.0729 0.9786 0.0190
-11.000 -0.9262 0.02053 0.01546 -0.0731 0.9737 0.0192
-10.750 -0.9038 0.01988 0.01473 -0.0731 0.9693 0.0194
-10.500 -0.8848 0.01855 0.01336 -0.0731 0.9649 0.0199
-10.250 -0.8613 0.01781 0.01260 -0.0733 0.9614 0.0202
-10.000 -0.8374 0.01718 0.01194 -0.0734 0.9578 0.0206
-9.750 -0.8136 0.01659 0.01130 -0.0734 0.9546 0.0209
-9.500 -0.7892 0.01604 0.01069 -0.0735 0.9513 0.0212
-9.250 -0.7630 0.01546 0.01007 -0.0738 0.9486 0.0215
-9.000 -0.7371 0.01491 0.00948 -0.0741 0.9454 0.0218
-8.750 -0.7111 0.01446 0.00898 -0.0742 0.9422 0.0221
-8.500 -0.6850 0.01407 0.00854 -0.0742 0.9394 0.0224
-8.250 -0.6593 0.01340 0.00782 -0.0745 0.9364 0.0227
-8.000 -0.6316 0.01278 0.00718 -0.0751 0.9341 0.0232
-7.750 -0.6038 0.01233 0.00671 -0.0755 0.9315 0.0236
-7.500 -0.5759 0.01193 0.00628 -0.0759 0.9288 0.0241
-7.250 -0.5480 0.01156 0.00589 -0.0762 0.9263 0.0247
-7.000 -0.5200 0.01125 0.00555 -0.0764 0.9240 0.0254
-6.750 -0.4920 0.01085 0.00511 -0.0767 0.9217 0.0264
-6.500 -0.4635 0.01053 0.00479 -0.0771 0.9194 0.0276
-6.250 -0.4344 0.01025 0.00449 -0.0775 0.9170 0.0290
-6.000 -0.4054 0.00991 0.00416 -0.0780 0.9144 0.0315
-5.750 -0.3764 0.00961 0.00388 -0.0784 0.9118 0.0359
-5.500 -0.3475 0.00928 0.00360 -0.0788 0.9094 0.0456
-5.250 -0.3185 0.00889 0.00329 -0.0793 0.9072 0.0624
-5.000 -0.2894 0.00842 0.00301 -0.0799 0.9050 0.1028
-4.750 -0.2602 0.00811 0.00281 -0.0804 0.9026 0.1296
-4.500 -0.2302 0.00771 0.00258 -0.0812 0.9006 0.1688
-4.250 -0.2002 0.00732 0.00239 -0.0819 0.8982 0.2143
-4.000 -0.1703 0.00696 0.00221 -0.0826 0.8958 0.2600
-3.750 -0.1405 0.00664 0.00205 -0.0832 0.8933 0.3076
-3.500 -0.1106 0.00631 0.00190 -0.0839 0.8910 0.3594
-3.250 -0.0811 0.00605 0.00179 -0.0843 0.8882 0.4066
-3.000 -0.0518 0.00588 0.00173 -0.0846 0.8849 0.4474
-2.750 -0.0218 0.00573 0.00168 -0.0851 0.8823 0.4756
-2.500 0.0079 0.00564 0.00164 -0.0854 0.8791 0.4945
-2.250 0.0372 0.00556 0.00158 -0.0855 0.8747 0.5096
-2.000 0.0659 0.00550 0.00150 -0.0854 0.8693 0.5232
-1.750 0.0949 0.00542 0.00146 -0.0855 0.8630 0.5358
-1.500 0.1240 0.00536 0.00139 -0.0856 0.8557 0.5463
-1.250 0.1526 0.00533 0.00134 -0.0855 0.8480 0.5569
-1.000 0.1820 0.00528 0.00130 -0.0856 0.8396 0.5658
-0.750 0.2109 0.00525 0.00128 -0.0856 0.8316 0.5749
-0.500 0.2403 0.00525 0.00127 -0.0857 0.8240 0.5832
-0.250 0.2695 0.00523 0.00126 -0.0858 0.8145 0.5911
0.000 0.2986 0.00523 0.00126 -0.0859 0.8057 0.5988
0.250 0.3278 0.00526 0.00126 -0.0859 0.7945 0.6051
0.500 0.3570 0.00526 0.00128 -0.0860 0.7829 0.6121
0.750 0.3859 0.00530 0.00130 -0.0861 0.7686 0.6186
1.000 0.4147 0.00537 0.00131 -0.0861 0.7474 0.6242
1.250 0.4427 0.00551 0.00133 -0.0859 0.7073 0.6296
1.500 0.4695 0.00582 0.00143 -0.0856 0.6542 0.6351
1.750 0.4925 0.00675 0.00171 -0.0849 0.4892 0.6402
2.000 0.5170 0.00752 0.00198 -0.0845 0.3711 0.6448
2.250 0.5427 0.00809 0.00221 -0.0843 0.2876 0.6492
2.500 0.5687 0.00857 0.00243 -0.0841 0.2222 0.6543
2.750 0.5956 0.00892 0.00262 -0.0840 0.1844 0.6589
3.000 0.6231 0.00920 0.00279 -0.0839 0.1630 0.6635
3.250 0.6508 0.00944 0.00295 -0.0839 0.1474 0.6673
3.500 0.6785 0.00963 0.00310 -0.0838 0.1356 0.6719
3.750 0.7063 0.00981 0.00327 -0.0838 0.1263 0.6764
4.000 0.7340 0.01000 0.00344 -0.0837 0.1184 0.6806
4.250 0.7616 0.01021 0.00362 -0.0836 0.1110 0.6847
4.500 0.7891 0.01044 0.00381 -0.0835 0.1034 0.6882
4.750 0.8166 0.01062 0.00398 -0.0834 0.0931 0.6926
5.000 0.8434 0.01090 0.00419 -0.0832 0.0790 0.6966
5.250 0.8687 0.01139 0.00453 -0.0829 0.0518 0.7006
5.500 0.8940 0.01189 0.00493 -0.0825 0.0356 0.7045
5.750 0.9201 0.01228 0.00529 -0.0821 0.0302 0.7078
6.000 0.9464 0.01261 0.00562 -0.0818 0.0274 0.7118
6.250 0.9728 0.01291 0.00594 -0.0815 0.0256 0.7159
6.500 0.9989 0.01326 0.00631 -0.0812 0.0243 0.7197
6.750 1.0250 0.01359 0.00666 -0.0808 0.0233 0.7234
7.000 1.0506 0.01398 0.00704 -0.0804 0.0223 0.7269
7.250 1.0759 0.01439 0.00749 -0.0800 0.0214 0.7307
7.500 1.1015 0.01472 0.00785 -0.0796 0.0204 0.7347
7.750 1.1264 0.01514 0.00830 -0.0791 0.0194 0.7384
8.000 1.1506 0.01566 0.00886 -0.0786 0.0186 0.7422
8.250 1.1756 0.01606 0.00929 -0.0781 0.0179 0.7460
8.500 1.2001 0.01650 0.00977 -0.0775 0.0173 0.7498
8.750 1.2236 0.01702 0.01034 -0.0769 0.0167 0.7539
9.000 1.2447 0.01785 0.01122 -0.0759 0.0161 0.7577
9.250 1.2688 0.01826 0.01170 -0.0753 0.0157 0.7619
9.500 1.2920 0.01877 0.01225 -0.0746 0.0153 0.7658
9.750 1.3147 0.01928 0.01284 -0.0738 0.0149 0.7703
10.000 1.3368 0.01983 0.01345 -0.0730 0.0145 0.7748
10.250 1.3583 0.02042 0.01408 -0.0721 0.0142 0.7794
10.500 1.3780 0.02117 0.01487 -0.0710 0.0139 0.7839
10.750 1.3936 0.02229 0.01608 -0.0693 0.0135 0.7892
11.000 1.4148 0.02278 0.01666 -0.0683 0.0133 0.7949
11.250 1.4349 0.02335 0.01732 -0.0673 0.0131 0.8005
11.500 1.4539 0.02397 0.01803 -0.0660 0.0128 0.8067
11.750 1.4721 0.02461 0.01877 -0.0647 0.0125 0.8145
12.000 1.4884 0.02521 0.01946 -0.0631 0.0121 0.8235
12.250 1.5037 0.02581 0.02014 -0.0614 0.0119 0.8358
12.500 1.5189 0.02640 0.02083 -0.0597 0.0116 0.8553
12.750 1.5243 0.02703 0.02171 -0.0564 0.0113 1.0000
13.000 1.5307 0.02838 0.02314 -0.0539 0.0110 1.0000
13.250 1.5476 0.02897 0.02380 -0.0527 0.0108 1.0000
13.500 1.5611 0.02981 0.02472 -0.0511 0.0105 1.0000
13.750 1.5730 0.03078 0.02577 -0.0495 0.0102 1.0000
14.000 1.5859 0.03168 0.02673 -0.0480 0.0099 1.0000
14.250 1.5975 0.03270 0.02781 -0.0465 0.0097 1.0000
14.500 1.6070 0.03391 0.02908 -0.0450 0.0095 1.0000
14.750 1.6158 0.03519 0.03043 -0.0435 0.0093 1.0000
15.000 1.6212 0.03682 0.03213 -0.0419 0.0091 1.0000
15.250 1.6220 0.03890 0.03429 -0.0402 0.0089 1.0000
15.500 1.6170 0.04162 0.03713 -0.0385 0.0087 1.0000
15.750 1.6182 0.04388 0.03951 -0.0373 0.0086 1.0000
16.000 1.6172 0.04646 0.04221 -0.0364 0.0085 1.0000
16.250 1.6136 0.04947 0.04535 -0.0358 0.0084 1.0000
16.500 1.6083 0.05285 0.04886 -0.0356 0.0083 1.0000
16.750 1.5978 0.05715 0.05330 -0.0360 0.0083 1.0000
17.000 1.5881 0.06167 0.05796 -0.0370 0.0082 1.0000
17.250 1.5730 0.06745 0.06389 -0.0390 0.0081 1.0000
17.500 1.5496 0.07532 0.07195 -0.0428 0.0081 1.0000
17.750 1.5215 0.08493 0.08175 -0.0482 0.0081 1.0000
18.000 1.4722 0.09940 0.09648 -0.0566 0.0082 1.0000
18.250 1.4183 0.11469 0.11200 -0.0652 0.0083 1.0000
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