WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL (whitcomb-il) Reynolds number: 50,000 Max Cl/Cd: 22.05 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-whitcomb-il-50000.txt Download as CSV file: xf-whitcomb-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: WHITCOMB INTEGRAL SUPERCRITICAL AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4919 0.11019 0.10208 -0.0018 1.0000 0.3744
-8.500 -0.6769 0.08007 0.07228 -0.0307 1.0000 0.1763
-8.250 -0.7043 0.07293 0.06508 -0.0338 1.0000 0.1685
-8.000 -0.7573 0.06206 0.05348 -0.0417 1.0000 0.1561
-7.750 -0.7521 0.05718 0.04827 -0.0431 1.0000 0.1559
-7.500 -0.7414 0.05243 0.04303 -0.0451 1.0000 0.1564
-7.250 -0.7244 0.04809 0.03832 -0.0464 1.0000 0.1574
-7.000 -0.7049 0.04511 0.03534 -0.0461 1.0000 0.1607
-6.750 -0.6830 0.04234 0.03235 -0.0467 1.0000 0.1660
-6.500 -0.6565 0.03911 0.02855 -0.0486 1.0000 0.1712
-6.250 -0.6315 0.03651 0.02577 -0.0490 1.0000 0.1779
-6.000 -0.6051 0.03449 0.02353 -0.0493 1.0000 0.1872
-5.750 -0.5798 0.03248 0.02144 -0.0491 1.0000 0.1970
-5.500 -0.5534 0.03074 0.01954 -0.0489 1.0000 0.2108
-5.250 -0.5290 0.02927 0.01803 -0.0480 1.0000 0.2274
-5.000 -0.5081 0.02799 0.01695 -0.0459 1.0000 0.2476
-4.750 -0.4873 0.02681 0.01598 -0.0438 1.0000 0.2759
-4.500 -0.4662 0.02547 0.01500 -0.0420 1.0000 0.3181
-4.250 -0.4465 0.02387 0.01429 -0.0400 1.0000 0.3929
-4.000 -0.4493 0.02429 0.01602 -0.0298 1.0000 0.4916
-3.750 -0.4560 0.02751 0.01962 -0.0158 1.0000 0.5675
-3.500 -0.4426 0.03092 0.02281 -0.0082 1.0000 0.6580
-3.250 -0.4348 0.03274 0.02446 -0.0003 1.0000 0.7044
-3.000 -0.4296 0.03358 0.02520 0.0082 1.0000 0.7387
-2.750 -0.4220 0.03378 0.02529 0.0156 1.0000 0.7735
-2.500 -0.4113 0.03348 0.02487 0.0218 1.0000 0.8100
-2.250 -0.3970 0.03280 0.02405 0.0267 1.0000 0.8479
-2.000 -0.3654 0.03176 0.02282 0.0284 1.0000 0.8885
-1.750 -0.2247 0.03003 0.02058 0.0099 1.0000 0.9479
-1.500 -0.0788 0.02806 0.01822 -0.0134 1.0000 0.9929
-1.250 -0.0427 0.02736 0.01745 -0.0166 1.0000 1.0000
-1.000 -0.0326 0.02696 0.01706 -0.0147 1.0000 1.0000
-0.750 -0.0226 0.02661 0.01671 -0.0127 1.0000 1.0000
-0.500 -0.0125 0.02629 0.01641 -0.0106 1.0000 1.0000
-0.250 -0.0026 0.02600 0.01615 -0.0085 1.0000 1.0000
0.000 0.0072 0.02574 0.01593 -0.0064 1.0000 1.0000
0.250 0.0167 0.02551 0.01574 -0.0042 1.0000 1.0000
0.500 0.0261 0.02531 0.01559 -0.0019 1.0000 1.0000
0.750 0.0351 0.02513 0.01548 0.0004 1.0000 1.0000
1.000 0.0438 0.02497 0.01540 0.0028 1.0000 1.0000
1.250 0.0521 0.02484 0.01534 0.0052 1.0000 1.0000
1.500 0.0600 0.02473 0.01532 0.0076 1.0000 1.0000
1.750 0.0673 0.02464 0.01534 0.0101 1.0000 1.0000
2.000 0.0741 0.02458 0.01539 0.0126 1.0000 1.0000
2.250 0.0803 0.02454 0.01548 0.0151 1.0000 1.0000
2.500 0.0859 0.02454 0.01560 0.0176 1.0000 1.0000
2.750 0.0909 0.02458 0.01579 0.0200 1.0000 1.0000
3.000 0.0953 0.02468 0.01604 0.0223 1.0000 1.0000
3.250 0.1009 0.02491 0.01644 0.0241 1.0000 1.0000
3.500 0.1090 0.02535 0.01707 0.0250 1.0000 1.0000
3.750 0.3861 0.02316 0.01616 -0.0110 0.8140 1.0000
4.000 0.6106 0.02769 0.01665 -0.0381 0.2269 1.0000
4.250 0.6404 0.02910 0.01805 -0.0384 0.2077 1.0000
4.500 0.6666 0.03064 0.01955 -0.0381 0.1942 1.0000
4.750 0.6881 0.03202 0.02118 -0.0369 0.1841 1.0000
5.000 0.7084 0.03375 0.02301 -0.0357 0.1762 1.0000
5.250 0.7248 0.03545 0.02510 -0.0335 0.1710 1.0000
5.500 0.7406 0.03714 0.02696 -0.0315 0.1657 1.0000
5.750 0.7562 0.03937 0.02921 -0.0299 0.1610 1.0000
6.000 0.7630 0.04131 0.03164 -0.0263 0.1593 1.0000
6.250 0.7686 0.04355 0.03426 -0.0228 0.1586 1.0000
6.500 0.7708 0.04581 0.03690 -0.0190 0.1580 1.0000
6.750 0.7696 0.04811 0.03957 -0.0148 0.1575 1.0000
7.000 0.7669 0.05056 0.04235 -0.0108 0.1573 1.0000
7.250 0.7661 0.05342 0.04554 -0.0076 0.1579 1.0000
7.500 0.7710 0.05695 0.04930 -0.0057 0.1596 1.0000
7.750 0.7508 0.06207 0.05519 -0.0031 0.1696 1.0000
8.000 0.7577 0.06726 0.06053 -0.0033 0.1768 1.0000
8.250 0.6109 0.06508 0.05918 0.0081 0.1921 1.0000
8.500 0.6066 0.10281 0.09708 -0.0415 0.3994 1.0000
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Polar data table (+)
Polar graphs
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