NYU/GRUMMAN K-1 AIRFOIL (k1-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NYU/GRUMMAN K-1 AIRFOIL (k1-il) Reynolds number: 500,000 Max Cl/Cd: 63.5 at α=5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-k1-il-500000-n5.txt Download as CSV file: xf-k1-il-500000-n5.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 = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-16.750 -0.8983 0.12167 0.11884 -0.0088 1.0000 0.0151
-16.500 -0.9633 0.10299 0.09986 -0.0196 1.0000 0.0150
-16.250 -0.9928 0.09272 0.08940 -0.0258 1.0000 0.0150
-16.000 -1.0144 0.08440 0.08090 -0.0310 1.0000 0.0150
-15.750 -1.0313 0.07723 0.07358 -0.0355 1.0000 0.0151
-15.500 -1.0445 0.07096 0.06715 -0.0394 1.0000 0.0152
-15.250 -1.0551 0.06538 0.06142 -0.0429 1.0000 0.0153
-15.000 -1.0636 0.06044 0.05633 -0.0459 1.0000 0.0154
-14.750 -1.0701 0.05601 0.05175 -0.0486 1.0000 0.0155
-14.500 -1.0743 0.05203 0.04763 -0.0508 1.0000 0.0156
-14.250 -1.0765 0.04843 0.04388 -0.0528 1.0000 0.0157
-14.000 -1.0766 0.04517 0.04048 -0.0546 1.0000 0.0159
-13.750 -1.0745 0.04225 0.03742 -0.0561 1.0000 0.0160
-13.500 -1.0704 0.03962 0.03465 -0.0574 1.0000 0.0161
-13.250 -1.0641 0.03726 0.03214 -0.0586 1.0000 0.0163
-13.000 -1.0558 0.03514 0.02988 -0.0597 1.0000 0.0165
-12.750 -1.0476 0.03307 0.02775 -0.0606 1.0000 0.0167
-12.500 -1.0366 0.03131 0.02594 -0.0614 1.0000 0.0169
-12.250 -1.0240 0.02975 0.02433 -0.0623 1.0000 0.0171
-12.000 -1.0113 0.02833 0.02285 -0.0629 0.9991 0.0173
-11.750 -0.9899 0.02689 0.02132 -0.0652 0.9867 0.0176
-11.500 -0.9656 0.02550 0.01983 -0.0676 0.9806 0.0178
-11.250 -0.9426 0.02427 0.01850 -0.0693 0.9748 0.0181
-11.000 -0.9201 0.02321 0.01734 -0.0703 0.9697 0.0184
-10.750 -0.8975 0.02227 0.01630 -0.0710 0.9655 0.0186
-10.500 -0.8755 0.02141 0.01534 -0.0713 0.9608 0.0189
-10.250 -0.8527 0.02065 0.01448 -0.0716 0.9566 0.0192
-10.000 -0.8299 0.01985 0.01361 -0.0718 0.9530 0.0195
-9.750 -0.8066 0.01903 0.01276 -0.0722 0.9499 0.0199
-9.500 -0.7820 0.01833 0.01202 -0.0727 0.9466 0.0202
-9.250 -0.7571 0.01767 0.01132 -0.0730 0.9434 0.0205
-9.000 -0.7320 0.01706 0.01065 -0.0733 0.9404 0.0209
-8.750 -0.7066 0.01648 0.01002 -0.0735 0.9378 0.0213
-8.500 -0.6805 0.01594 0.00942 -0.0738 0.9354 0.0217
-8.250 -0.6535 0.01543 0.00885 -0.0743 0.9325 0.0222
-8.000 -0.6267 0.01489 0.00828 -0.0747 0.9292 0.0227
-7.750 -0.6001 0.01439 0.00776 -0.0750 0.9260 0.0234
-7.500 -0.5731 0.01395 0.00728 -0.0752 0.9233 0.0240
-7.250 -0.5459 0.01355 0.00684 -0.0754 0.9210 0.0248
-7.000 -0.5179 0.01318 0.00643 -0.0758 0.9187 0.0257
-6.750 -0.4895 0.01277 0.00601 -0.0764 0.9161 0.0268
-6.500 -0.4610 0.01243 0.00566 -0.0768 0.9135 0.0284
-6.250 -0.4327 0.01209 0.00531 -0.0772 0.9108 0.0303
-6.000 -0.4044 0.01178 0.00499 -0.0775 0.9081 0.0333
-5.750 -0.3763 0.01147 0.00469 -0.0777 0.9055 0.0380
-5.500 -0.3482 0.01118 0.00441 -0.0779 0.9031 0.0449
-5.250 -0.3190 0.01086 0.00412 -0.0785 0.9003 0.0539
-5.000 -0.2899 0.01047 0.00383 -0.0791 0.8975 0.0715
-4.750 -0.2607 0.01007 0.00358 -0.0797 0.8948 0.1039
-4.500 -0.2315 0.00972 0.00333 -0.0802 0.8923 0.1294
-4.250 -0.2023 0.00931 0.00309 -0.0809 0.8900 0.1685
-3.750 -0.1435 0.00840 0.00262 -0.0823 0.8857 0.2801
-3.500 -0.1135 0.00799 0.00245 -0.0831 0.8834 0.3425
-3.250 -0.0835 0.00772 0.00235 -0.0838 0.8808 0.3884
-3.000 -0.0537 0.00755 0.00227 -0.0843 0.8780 0.4207
-2.750 -0.0240 0.00741 0.00221 -0.0846 0.8753 0.4470
-2.500 0.0054 0.00731 0.00217 -0.0849 0.8727 0.4681
-2.250 0.0348 0.00724 0.00212 -0.0851 0.8702 0.4848
-2.000 0.0638 0.00717 0.00208 -0.0852 0.8673 0.5027
-1.750 0.0933 0.00711 0.00207 -0.0855 0.8632 0.5188
-1.500 0.1224 0.00705 0.00205 -0.0856 0.8573 0.5316
-1.250 0.1509 0.00700 0.00198 -0.0855 0.8505 0.5440
-1.000 0.1796 0.00694 0.00195 -0.0854 0.8423 0.5548
-0.750 0.2080 0.00690 0.00187 -0.0852 0.8309 0.5640
-0.500 0.2363 0.00685 0.00183 -0.0851 0.8163 0.5725
-0.250 0.2648 0.00684 0.00179 -0.0849 0.8013 0.5812
0.000 0.2933 0.00684 0.00176 -0.0848 0.7855 0.5885
0.250 0.3216 0.00686 0.00175 -0.0847 0.7653 0.5958
0.500 0.3499 0.00691 0.00174 -0.0845 0.7400 0.6027
0.750 0.3776 0.00702 0.00174 -0.0843 0.7046 0.6083
1.000 0.4046 0.00723 0.00179 -0.0839 0.6667 0.6142
1.250 0.4303 0.00764 0.00190 -0.0834 0.5862 0.6199
1.750 0.4783 0.00905 0.00242 -0.0824 0.3770 0.6300
2.000 0.5040 0.00954 0.00265 -0.0821 0.3102 0.6351
2.250 0.5303 0.00997 0.00286 -0.0819 0.2580 0.6403
2.500 0.5566 0.01040 0.00307 -0.0818 0.2102 0.6452
2.750 0.5834 0.01072 0.00327 -0.0816 0.1819 0.6496
3.000 0.6105 0.01099 0.00347 -0.0815 0.1638 0.6541
3.250 0.6377 0.01125 0.00368 -0.0814 0.1484 0.6588
3.500 0.6649 0.01149 0.00387 -0.0812 0.1355 0.6636
3.750 0.6923 0.01174 0.00406 -0.0812 0.1249 0.6680
4.000 0.7194 0.01195 0.00427 -0.0810 0.1161 0.6718
4.250 0.7464 0.01219 0.00450 -0.0808 0.1077 0.6760
4.500 0.7735 0.01242 0.00473 -0.0807 0.0993 0.6805
4.750 0.8003 0.01269 0.00495 -0.0805 0.0873 0.6848
5.000 0.8268 0.01302 0.00520 -0.0803 0.0739 0.6887
5.250 0.8520 0.01346 0.00554 -0.0799 0.0528 0.6924
5.500 0.8772 0.01391 0.00593 -0.0795 0.0400 0.6964
5.750 0.9028 0.01432 0.00633 -0.0791 0.0334 0.7003
6.000 0.9285 0.01470 0.00671 -0.0787 0.0295 0.7044
6.250 0.9543 0.01508 0.00709 -0.0784 0.0268 0.7085
6.500 0.9797 0.01546 0.00750 -0.0779 0.0248 0.7120
6.750 1.0051 0.01583 0.00791 -0.0775 0.0234 0.7156
7.000 1.0302 0.01624 0.00834 -0.0771 0.0223 0.7195
7.250 1.0550 0.01669 0.00882 -0.0766 0.0214 0.7237
7.500 1.0798 0.01713 0.00930 -0.0761 0.0207 0.7277
7.750 1.1042 0.01759 0.00981 -0.0755 0.0200 0.7312
8.000 1.1280 0.01810 0.01037 -0.0749 0.0194 0.7347
8.250 1.1510 0.01870 0.01101 -0.0742 0.0188 0.7388
8.500 1.1746 0.01920 0.01158 -0.0735 0.0182 0.7431
8.750 1.1978 0.01974 0.01218 -0.0729 0.0175 0.7472
9.000 1.2204 0.02030 0.01280 -0.0721 0.0168 0.7508
9.250 1.2415 0.02101 0.01355 -0.0712 0.0162 0.7547
9.500 1.2632 0.02162 0.01425 -0.0703 0.0157 0.7593
9.750 1.2846 0.02225 0.01497 -0.0694 0.0153 0.7640
10.000 1.3053 0.02289 0.01570 -0.0684 0.0148 0.7682
10.250 1.3254 0.02355 0.01644 -0.0673 0.0143 0.7726
10.500 1.3446 0.02426 0.01722 -0.0662 0.0139 0.7776
10.750 1.3613 0.02518 0.01820 -0.0648 0.0135 0.7830
11.000 1.3798 0.02585 0.01900 -0.0635 0.0132 0.7885
11.250 1.3967 0.02660 0.01987 -0.0620 0.0128 0.7948
11.500 1.4106 0.02739 0.02077 -0.0601 0.0125 0.8014
11.750 1.4243 0.02822 0.02173 -0.0583 0.0121 0.8086
12.000 1.4371 0.02912 0.02275 -0.0564 0.0119 0.8180
12.250 1.4488 0.03007 0.02382 -0.0545 0.0116 0.8300
12.500 1.4595 0.03105 0.02494 -0.0525 0.0114 0.8478
12.750 1.4624 0.03187 0.02601 -0.0491 0.0113 0.9671
13.000 1.4697 0.03326 0.02748 -0.0472 0.0111 1.0000
13.250 1.4772 0.03469 0.02902 -0.0454 0.0109 1.0000
13.500 1.4839 0.03622 0.03069 -0.0436 0.0107 1.0000
13.750 1.4891 0.03792 0.03252 -0.0419 0.0105 1.0000
14.000 1.4933 0.03976 0.03449 -0.0404 0.0103 1.0000
14.250 1.4958 0.04180 0.03666 -0.0389 0.0101 1.0000
14.500 1.4970 0.04405 0.03904 -0.0377 0.0100 1.0000
14.750 1.4971 0.04651 0.04163 -0.0367 0.0098 1.0000
15.000 1.4952 0.04930 0.04456 -0.0359 0.0097 1.0000
15.250 1.4920 0.05240 0.04779 -0.0356 0.0095 1.0000
15.500 1.4867 0.05593 0.05147 -0.0357 0.0094 1.0000
15.750 1.4792 0.06003 0.05571 -0.0363 0.0093 1.0000
16.000 1.4686 0.06487 0.06071 -0.0377 0.0093 1.0000
16.250 1.4538 0.07090 0.06691 -0.0402 0.0092 1.0000
16.500 1.4355 0.07825 0.07445 -0.0441 0.0092 1.0000
16.750 1.4095 0.08782 0.08423 -0.0497 0.0092 1.0000
17.000 1.3756 0.09955 0.09619 -0.0566 0.0092 1.0000
17.250 1.3356 0.11251 0.10937 -0.0640 0.0093 1.0000
17.500 1.2956 0.12542 0.12247 -0.0713 0.0093 1.0000
17.750 1.2597 0.13763 0.13483 -0.0784 0.0094 1.0000
18.000 1.2286 0.14935 0.14670 -0.0856 0.0094 1.0000
18.250 1.1988 0.16150 0.15900 -0.0933 0.0094 1.0000
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