GRUMMAN K-2 AIRFOIL (k2-il) Xfoil prediction polar at RE=500,000 Ncrit=9
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Airfoil: GRUMMAN K-2 AIRFOIL (k2-il) Reynolds number: 500,000 Max Cl/Cd: 44.01 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-k2-il-500000.txt Download as CSV file: xf-k2-il-500000.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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.7712 0.06480 0.06177 -0.0456 1.0000 0.0304
-9.250 -0.8104 0.06197 0.05878 -0.0414 1.0000 0.0305
-9.000 -0.8484 0.05958 0.05618 -0.0365 1.0000 0.0306
-8.750 -0.8678 0.05707 0.05341 -0.0331 1.0000 0.0308
-8.500 -0.9220 0.03964 0.03516 -0.0281 1.0000 0.0217
-8.250 -0.9178 0.03643 0.03175 -0.0263 1.0000 0.0212
-8.000 -0.9132 0.03231 0.02724 -0.0244 1.0000 0.0205
-7.750 -0.9032 0.02829 0.02273 -0.0228 1.0000 0.0200
-7.500 -0.8863 0.02597 0.02012 -0.0217 1.0000 0.0201
-7.250 -0.8668 0.02429 0.01822 -0.0208 1.0000 0.0202
-7.000 -0.8459 0.02284 0.01660 -0.0201 1.0000 0.0204
-6.750 -0.8240 0.02163 0.01524 -0.0194 1.0000 0.0207
-6.500 -0.8014 0.02056 0.01404 -0.0187 1.0000 0.0210
-6.250 -0.7780 0.01961 0.01298 -0.0182 1.0000 0.0213
-6.000 -0.7541 0.01880 0.01207 -0.0177 1.0000 0.0217
-5.750 -0.7296 0.01816 0.01134 -0.0173 1.0000 0.0220
-5.500 -0.7054 0.01699 0.01017 -0.0171 1.0000 0.0227
-5.250 -0.6803 0.01643 0.00964 -0.0170 1.0000 0.0235
-5.000 -0.6546 0.01598 0.00917 -0.0170 1.0000 0.0245
-4.750 -0.6284 0.01552 0.00868 -0.0170 1.0000 0.0256
-4.500 -0.6010 0.01483 0.00797 -0.0173 1.0000 0.0267
-4.250 -0.5732 0.01429 0.00747 -0.0178 1.0000 0.0281
-4.000 -0.5453 0.01391 0.00707 -0.0182 1.0000 0.0298
-3.750 -0.5158 0.01338 0.00654 -0.0189 1.0000 0.0319
-3.500 -0.4873 0.01305 0.00625 -0.0195 1.0000 0.0346
-3.250 -0.4576 0.01267 0.00589 -0.0202 1.0000 0.0383
-3.000 -0.4289 0.01246 0.00568 -0.0207 1.0000 0.0424
-2.750 -0.3982 0.01209 0.00536 -0.0217 1.0000 0.0492
-2.500 -0.3664 0.01171 0.00509 -0.0229 1.0000 0.0634
-2.250 -0.3247 0.01074 0.00472 -0.0269 1.0000 0.1800
-2.000 -0.2508 0.00869 0.00419 -0.0389 1.0000 0.5257
-1.750 -0.2093 0.00830 0.00437 -0.0420 1.0000 0.6669
-1.500 -0.1819 0.00842 0.00457 -0.0419 1.0000 0.7013
-1.250 -0.1564 0.00861 0.00479 -0.0413 1.0000 0.7205
-1.000 -0.1304 0.00881 0.00500 -0.0408 1.0000 0.7354
-0.750 -0.0930 0.00918 0.00541 -0.0424 0.9963 0.7528
-0.500 -0.0516 0.00964 0.00589 -0.0445 0.9903 0.7678
-0.250 -0.0023 0.00980 0.00609 -0.0484 0.9841 0.7716
0.000 0.0354 0.00977 0.00608 -0.0499 0.9762 0.7748
0.250 0.0797 0.00964 0.00596 -0.0527 0.9691 0.7784
0.500 0.1243 0.00944 0.00575 -0.0558 0.9615 0.7849
0.750 0.1529 0.00945 0.00582 -0.0551 0.9549 0.7877
1.000 0.1841 0.00943 0.00585 -0.0551 0.9488 0.7903
1.250 0.2224 0.00927 0.00574 -0.0568 0.9446 0.7925
1.500 0.2503 0.00910 0.00561 -0.0563 0.9345 0.7952
1.750 0.2831 0.00884 0.00538 -0.0569 0.9210 0.7981
2.000 0.3266 0.00849 0.00501 -0.0598 0.8917 0.8010
2.250 0.3739 0.00879 0.00457 -0.0630 0.7041 0.8025
2.500 0.3830 0.00993 0.00485 -0.0589 0.5065 0.8041
2.750 0.3999 0.01082 0.00511 -0.0567 0.3539 0.8057
3.000 0.4213 0.01148 0.00533 -0.0555 0.2539 0.8075
3.250 0.4448 0.01204 0.00554 -0.0548 0.1768 0.8094
3.500 0.4704 0.01240 0.00572 -0.0544 0.1386 0.8116
3.750 0.4978 0.01269 0.00589 -0.0544 0.1160 0.8140
4.000 0.5272 0.01292 0.00605 -0.0549 0.0997 0.8166
4.250 0.5580 0.01316 0.00620 -0.0557 0.0817 0.8193
4.500 0.5809 0.01370 0.00648 -0.0547 0.0389 0.8207
4.750 0.6042 0.01431 0.00701 -0.0536 0.0267 0.8220
5.000 0.6289 0.01478 0.00749 -0.0529 0.0230 0.8234
5.250 0.6543 0.01514 0.00788 -0.0522 0.0210 0.8251
5.500 0.6790 0.01567 0.00840 -0.0516 0.0195 0.8269
5.750 0.7048 0.01616 0.00895 -0.0511 0.0185 0.8289
6.000 0.7315 0.01667 0.00948 -0.0509 0.0176 0.8309
6.250 0.7588 0.01724 0.01005 -0.0510 0.0169 0.8331
6.500 0.7861 0.01813 0.01092 -0.0512 0.0163 0.8355
6.750 0.8084 0.01902 0.01188 -0.0500 0.0160 0.8368
7.000 0.8320 0.01975 0.01270 -0.0491 0.0157 0.8380
7.250 0.8557 0.02062 0.01366 -0.0482 0.0156 0.8393
7.500 0.8793 0.02164 0.01479 -0.0473 0.0155 0.8408
7.750 0.9027 0.02280 0.01609 -0.0464 0.0155 0.8424
8.000 0.9260 0.02409 0.01753 -0.0456 0.0154 0.8443
8.250 0.9493 0.02545 0.01910 -0.0448 0.0153 0.8462
8.500 0.9722 0.02695 0.02082 -0.0441 0.0152 0.8480
8.750 0.9942 0.02870 0.02282 -0.0433 0.0151 0.8498
9.000 1.0138 0.03091 0.02533 -0.0423 0.0152 0.8515
9.250 1.0269 0.03340 0.02814 -0.0401 0.0154 0.8528
9.500 1.0373 0.03610 0.03115 -0.0377 0.0156 0.8543
9.750 1.0451 0.03935 0.03465 -0.0353 0.0159 0.8559
10.000 0.8819 0.07122 0.06885 -0.0210 0.0255 0.8588
10.250 0.8511 0.07889 0.07669 -0.0226 0.0253 0.8609
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Polar data table (+)
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