RAE 2822 AIRFOIL (rae2822-il) Xfoil prediction polar at RE=200,000 Ncrit=9
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Airfoil: RAE 2822 AIRFOIL (rae2822-il) Reynolds number: 200,000 Max Cl/Cd: 53.63 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae2822-il-200000.txt Download as CSV file: xf-rae2822-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: RAE 2822 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.4643 0.09944 0.09591 -0.0418 1.0000 0.0732
-11.500 -0.5733 0.06898 0.06531 -0.0586 1.0000 0.0441
-11.250 -0.5964 0.06239 0.05867 -0.0604 1.0000 0.0425
-11.000 -0.6289 0.05578 0.05195 -0.0622 1.0000 0.0411
-10.750 -0.7246 0.04764 0.04326 -0.0619 1.0000 0.0365
-10.500 -0.7424 0.04670 0.04220 -0.0585 1.0000 0.0362
-10.250 -0.8067 0.05369 0.04895 -0.0544 1.0000 0.0351
-10.000 -0.8187 0.05010 0.04522 -0.0517 1.0000 0.0343
-9.750 -0.8296 0.04679 0.04170 -0.0485 1.0000 0.0337
-9.500 -0.8374 0.04352 0.03814 -0.0452 1.0000 0.0333
-9.250 -0.8404 0.04071 0.03504 -0.0420 1.0000 0.0335
-9.000 -0.8387 0.03829 0.03231 -0.0392 1.0000 0.0340
-8.750 -0.8336 0.03585 0.02955 -0.0365 1.0000 0.0345
-8.500 -0.8256 0.03341 0.02678 -0.0341 1.0000 0.0348
-8.250 -0.8142 0.03122 0.02428 -0.0319 1.0000 0.0352
-8.000 -0.8005 0.02957 0.02234 -0.0299 1.0000 0.0357
-7.750 -0.7854 0.02683 0.01936 -0.0282 1.0000 0.0367
-7.500 -0.7695 0.02522 0.01777 -0.0268 1.0000 0.0390
-7.250 -0.7528 0.02430 0.01676 -0.0254 1.0000 0.0413
-7.000 -0.7350 0.02321 0.01555 -0.0239 1.0000 0.0434
-6.750 -0.7167 0.02230 0.01451 -0.0224 1.0000 0.0454
-6.500 -0.7005 0.02078 0.01299 -0.0208 1.0000 0.0486
-6.250 -0.6829 0.02004 0.01227 -0.0196 1.0000 0.0529
-6.000 -0.6641 0.01938 0.01151 -0.0184 1.0000 0.0569
-5.750 -0.6469 0.01822 0.01041 -0.0174 1.0000 0.0628
-5.500 -0.6240 0.01748 0.00965 -0.0173 0.9993 0.0722
-5.250 -0.5895 0.01649 0.00874 -0.0197 0.9960 0.0903
-5.000 -0.5555 0.01527 0.00780 -0.0223 0.9927 0.1407
-4.750 -0.5279 0.01280 0.00701 -0.0251 0.9894 0.4589
-4.500 -0.4921 0.01311 0.00735 -0.0268 0.9854 0.5305
-4.250 -0.4571 0.01349 0.00766 -0.0283 0.9814 0.5607
-4.000 -0.4250 0.01380 0.00794 -0.0290 0.9761 0.5798
-3.750 -0.3891 0.01416 0.00826 -0.0306 0.9723 0.5964
-3.500 -0.3555 0.01448 0.00854 -0.0317 0.9683 0.6105
-3.250 -0.3257 0.01473 0.00875 -0.0320 0.9627 0.6236
-3.000 -0.2911 0.01512 0.00916 -0.0330 0.9587 0.6387
-2.750 -0.2562 0.01559 0.00965 -0.0340 0.9555 0.6538
-2.500 -0.2306 0.01565 0.00968 -0.0336 0.9489 0.6610
-2.250 -0.1938 0.01551 0.00943 -0.0360 0.9451 0.6656
-2.000 -0.1554 0.01546 0.00937 -0.0383 0.9426 0.6686
-1.750 -0.1292 0.01542 0.00929 -0.0383 0.9362 0.6720
-1.500 -0.0949 0.01533 0.00915 -0.0399 0.9319 0.6764
-1.250 -0.0560 0.01522 0.00899 -0.0426 0.9291 0.6808
-1.000 -0.0202 0.01517 0.00894 -0.0443 0.9259 0.6837
-0.750 0.0048 0.01516 0.00894 -0.0440 0.9188 0.6874
-0.500 0.0428 0.01506 0.00883 -0.0463 0.9157 0.6922
-0.250 0.0835 0.01494 0.00871 -0.0491 0.9135 0.6964
0.000 0.1075 0.01497 0.00878 -0.0486 0.9063 0.6997
0.250 0.1441 0.01487 0.00873 -0.0504 0.9025 0.7039
0.500 0.1857 0.01473 0.00859 -0.0534 0.9000 0.7093
0.750 0.2269 0.01454 0.00849 -0.0559 0.8979 0.7130
1.000 0.2492 0.01456 0.00858 -0.0549 0.8889 0.7173
1.250 0.2896 0.01433 0.00840 -0.0573 0.8854 0.7224
1.500 0.3221 0.01418 0.00833 -0.0581 0.8793 0.7269
1.750 0.3559 0.01394 0.00820 -0.0589 0.8723 0.7315
2.000 0.3923 0.01359 0.00793 -0.0601 0.8646 0.7373
2.250 0.4317 0.01297 0.00737 -0.0613 0.8541 0.7420
2.500 0.4601 0.01239 0.00687 -0.0601 0.8332 0.7468
2.750 0.4901 0.01196 0.00646 -0.0595 0.8130 0.7530
3.000 0.5184 0.01168 0.00624 -0.0588 0.7942 0.7582
3.250 0.5427 0.01152 0.00615 -0.0574 0.7697 0.7644
3.500 0.5684 0.01137 0.00603 -0.0564 0.7398 0.7708
3.750 0.5915 0.01130 0.00595 -0.0548 0.6981 0.7766
4.000 0.6124 0.01142 0.00582 -0.0527 0.6179 0.7841
4.250 0.6163 0.01247 0.00594 -0.0477 0.4224 0.7904
4.500 0.6146 0.01455 0.00674 -0.0431 0.1820 0.7989
4.750 0.6252 0.01589 0.00758 -0.0402 0.1013 0.8060
5.000 0.6438 0.01669 0.00832 -0.0386 0.0819 0.8147
5.250 0.6617 0.01743 0.00909 -0.0368 0.0711 0.8232
5.500 0.6785 0.01847 0.01008 -0.0350 0.0635 0.8326
5.750 0.7001 0.01911 0.01086 -0.0337 0.0583 0.8434
6.000 0.7194 0.01998 0.01173 -0.0322 0.0531 0.8545
6.250 0.7409 0.02118 0.01303 -0.0310 0.0496 0.8659
6.500 0.7636 0.02215 0.01414 -0.0298 0.0468 0.8791
6.750 0.7847 0.02303 0.01512 -0.0284 0.0439 0.8950
7.000 0.8095 0.02557 0.01771 -0.0280 0.0405 0.9124
7.250 0.8306 0.02646 0.01891 -0.0264 0.0395 0.9410
7.500 0.8646 0.02858 0.02140 -0.0277 0.0383 1.0000
7.750 0.8917 0.03097 0.02412 -0.0279 0.0370 1.0000
8.000 0.9151 0.03291 0.02630 -0.0278 0.0350 1.0000
8.250 0.9337 0.03621 0.03002 -0.0267 0.0350 1.0000
8.500 0.9439 0.04095 0.03531 -0.0243 0.0365 1.0000
8.750 0.9493 0.04601 0.04077 -0.0220 0.0385 1.0000
9.750 0.9114 0.07306 0.06940 -0.0107 0.0629 1.0000
10.000 0.8771 0.07498 0.07158 -0.0064 0.0621 1.0000
10.250 0.8476 0.07866 0.07541 -0.0050 0.0615 1.0000
10.500 0.8210 0.08370 0.08056 -0.0062 0.0613 1.0000
10.750 0.7931 0.09038 0.08731 -0.0101 0.0612 1.0000
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Polar data table (+)
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