GRUMMAN K-2 AIRFOIL (k2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GRUMMAN K-2 AIRFOIL (k2-il) Reynolds number: 1,000,000 Max Cl/Cd: 60.36 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k2-il-1000000.txt Download as CSV file: xf-k2-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GRUMMAN K-2 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
------ -------- --------- --------- -------- -------- --------
-13.000 -0.9859 0.05546 0.05249 -0.0571 1.0000 0.0127
-12.750 -1.0036 0.05097 0.04783 -0.0578 1.0000 0.0126
-12.500 -1.0182 0.04739 0.04411 -0.0574 1.0000 0.0126
-12.250 -1.0322 0.04426 0.04083 -0.0562 1.0000 0.0126
-12.000 -1.0436 0.04170 0.03812 -0.0542 1.0000 0.0125
-11.750 -1.0557 0.03933 0.03561 -0.0516 1.0000 0.0125
-11.500 -1.0673 0.03725 0.03339 -0.0483 1.0000 0.0125
-11.250 -1.0794 0.03545 0.03146 -0.0443 1.0000 0.0125
-11.000 -1.0938 0.03406 0.02995 -0.0393 1.0000 0.0125
-10.750 -1.1030 0.03244 0.02819 -0.0351 1.0000 0.0125
-10.500 -1.1064 0.03013 0.02568 -0.0323 1.0000 0.0125
-10.250 -1.1049 0.02785 0.02318 -0.0298 1.0000 0.0126
-10.000 -1.0987 0.02584 0.02099 -0.0276 1.0000 0.0127
-9.750 -1.0873 0.02436 0.01938 -0.0259 1.0000 0.0128
-9.500 -1.0727 0.02320 0.01813 -0.0245 1.0000 0.0129
-9.250 -1.0560 0.02225 0.01710 -0.0234 1.0000 0.0131
-9.000 -1.0378 0.02140 0.01619 -0.0224 1.0000 0.0132
-8.750 -1.0184 0.02064 0.01536 -0.0215 1.0000 0.0134
-8.500 -0.9926 0.01986 0.01452 -0.0219 0.9995 0.0136
-8.250 -0.9646 0.01909 0.01368 -0.0227 0.9988 0.0138
-8.000 -0.9357 0.01836 0.01287 -0.0236 0.9979 0.0141
-7.750 -0.9064 0.01766 0.01211 -0.0246 0.9970 0.0143
-7.500 -0.8765 0.01699 0.01139 -0.0256 0.9962 0.0146
-7.250 -0.8461 0.01639 0.01073 -0.0267 0.9954 0.0148
-7.000 -0.8157 0.01583 0.01012 -0.0277 0.9948 0.0150
-6.750 -0.7852 0.01537 0.00962 -0.0287 0.9943 0.0152
-6.500 -0.7552 0.01453 0.00873 -0.0299 0.9939 0.0156
-6.250 -0.7277 0.01388 0.00805 -0.0304 0.9929 0.0160
-6.000 -0.6988 0.01346 0.00763 -0.0310 0.9919 0.0165
-5.750 -0.6688 0.01309 0.00725 -0.0318 0.9908 0.0170
-5.500 -0.6379 0.01275 0.00690 -0.0328 0.9898 0.0177
-5.250 -0.6065 0.01245 0.00658 -0.0338 0.9889 0.0183
-5.000 -0.5748 0.01196 0.00607 -0.0351 0.9882 0.0193
-4.750 -0.5430 0.01168 0.00581 -0.0362 0.9875 0.0204
-4.500 -0.5109 0.01146 0.00559 -0.0373 0.9869 0.0217
-4.250 -0.4778 0.01113 0.00528 -0.0387 0.9863 0.0236
-4.000 -0.4444 0.01093 0.00510 -0.0401 0.9857 0.0256
-3.750 -0.4104 0.01065 0.00484 -0.0416 0.9852 0.0283
-3.500 -0.3766 0.01047 0.00468 -0.0431 0.9847 0.0312
-3.250 -0.3426 0.01025 0.00450 -0.0446 0.9843 0.0358
-3.000 -0.3082 0.01005 0.00435 -0.0462 0.9839 0.0427
-2.750 -0.2774 0.00976 0.00416 -0.0471 0.9827 0.0563
-2.500 -0.2460 0.00935 0.00395 -0.0482 0.9815 0.0962
-2.250 -0.2059 0.00860 0.00372 -0.0518 0.9824 0.2152
-2.000 -0.1623 0.00784 0.00352 -0.0561 0.9838 0.3552
-1.750 -0.1191 0.00687 0.00324 -0.0606 0.9847 0.5326
-1.500 -0.0755 0.00639 0.00315 -0.0644 0.9846 0.6411
-1.250 -0.0366 0.00617 0.00304 -0.0666 0.9805 0.6792
-1.000 0.0087 0.00587 0.00279 -0.0699 0.9750 0.7022
-0.750 0.0566 0.00567 0.00267 -0.0738 0.9723 0.7283
-0.500 0.0879 0.00550 0.00251 -0.0741 0.9651 0.7372
-0.250 0.1280 0.00530 0.00233 -0.0764 0.9613 0.7420
0.000 0.1616 0.00521 0.00225 -0.0773 0.9577 0.7469
0.250 0.1896 0.00513 0.00216 -0.0771 0.9496 0.7508
0.500 0.2202 0.00502 0.00209 -0.0773 0.9419 0.7543
0.750 0.2516 0.00496 0.00204 -0.0777 0.9289 0.7581
1.000 0.2863 0.00493 0.00194 -0.0786 0.8908 0.7631
1.250 0.3116 0.00541 0.00193 -0.0775 0.7692 0.7674
1.500 0.3252 0.00643 0.00217 -0.0744 0.5761 0.7706
1.750 0.3459 0.00717 0.00239 -0.0729 0.4377 0.7729
2.000 0.3692 0.00778 0.00258 -0.0721 0.3307 0.7750
2.250 0.3940 0.00829 0.00275 -0.0715 0.2390 0.7772
2.500 0.4198 0.00875 0.00291 -0.0712 0.1699 0.7793
2.750 0.4467 0.00909 0.00306 -0.0710 0.1296 0.7815
3.000 0.4748 0.00931 0.00319 -0.0710 0.1098 0.7834
3.250 0.5030 0.00953 0.00333 -0.0711 0.0952 0.7850
3.500 0.5304 0.00970 0.00345 -0.0709 0.0822 0.7870
3.750 0.5573 0.00994 0.00361 -0.0707 0.0666 0.7885
4.000 0.5830 0.01036 0.00386 -0.0702 0.0346 0.7900
4.250 0.6091 0.01077 0.00420 -0.0698 0.0208 0.7916
4.500 0.6358 0.01110 0.00449 -0.0694 0.0167 0.7932
4.750 0.6630 0.01140 0.00481 -0.0692 0.0150 0.7949
5.000 0.6900 0.01172 0.00513 -0.0689 0.0138 0.7966
5.250 0.7168 0.01214 0.00556 -0.0686 0.0129 0.7984
5.500 0.7441 0.01247 0.00591 -0.0684 0.0123 0.8001
5.750 0.7712 0.01284 0.00629 -0.0682 0.0117 0.8014
6.000 0.7979 0.01322 0.00668 -0.0680 0.0113 0.8029
6.250 0.8234 0.01370 0.00720 -0.0674 0.0109 0.8044
6.500 0.8474 0.01441 0.00797 -0.0666 0.0106 0.8058
6.750 0.8710 0.01520 0.00882 -0.0657 0.0105 0.8071
7.000 0.8964 0.01566 0.00934 -0.0652 0.0103 0.8084
7.250 0.9216 0.01617 0.00990 -0.0646 0.0102 0.8098
7.500 0.9465 0.01674 0.01053 -0.0640 0.0101 0.8114
7.750 0.9711 0.01738 0.01123 -0.0634 0.0099 0.8130
8.000 0.9952 0.01812 0.01205 -0.0627 0.0098 0.8145
8.250 1.0190 0.01895 0.01295 -0.0620 0.0098 0.8160
8.500 1.0425 0.01984 0.01393 -0.0612 0.0097 0.8173
8.750 1.0655 0.02082 0.01501 -0.0604 0.0097 0.8185
9.000 1.0878 0.02185 0.01616 -0.0594 0.0097 0.8199
9.250 1.1087 0.02299 0.01745 -0.0583 0.0096 0.8214
9.500 1.1288 0.02420 0.01882 -0.0570 0.0096 0.8227
9.750 1.1475 0.02562 0.02042 -0.0555 0.0096 0.8239
10.000 1.1646 0.02721 0.02222 -0.0539 0.0096 0.8252
10.250 1.1800 0.02896 0.02419 -0.0520 0.0096 0.8265
10.500 1.1924 0.03107 0.02656 -0.0499 0.0096 0.8279
10.750 1.2021 0.03337 0.02912 -0.0474 0.0096 0.8294
11.000 1.2071 0.03608 0.03213 -0.0445 0.0096 0.8311
11.250 1.2055 0.03931 0.03569 -0.0411 0.0096 0.8327
11.500 1.1976 0.04284 0.03953 -0.0372 0.0096 0.8342
11.750 1.1756 0.04666 0.04365 -0.0317 0.0097 0.8355
12.000 1.1485 0.05074 0.04800 -0.0270 0.0098 0.8373
12.250 1.1187 0.05564 0.05315 -0.0243 0.0098 0.8388
12.500 1.0889 0.06177 0.05951 -0.0250 0.0099 0.8401
12.750 1.0541 0.07260 0.07057 -0.0338 0.0100 0.8415
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