RAE 5215 AIRFOIL (rae5215-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE 5215 AIRFOIL (rae5215-il) Reynolds number: 500,000 Max Cl/Cd: 68.64 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae5215-il-500000-n5.txt Download as CSV file: xf-rae5215-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE 5215 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.9188 0.04121 0.03777 -0.0489 1.0000 0.0090
-11.000 -0.9403 0.03378 0.02969 -0.0508 1.0000 0.0091
-10.750 -0.9354 0.02995 0.02544 -0.0510 1.0000 0.0092
-10.500 -0.9226 0.02722 0.02237 -0.0510 1.0000 0.0094
-10.250 -0.9058 0.02509 0.01994 -0.0508 1.0000 0.0096
-10.000 -0.8866 0.02335 0.01794 -0.0505 1.0000 0.0097
-9.750 -0.8654 0.02207 0.01652 -0.0503 1.0000 0.0099
-9.500 -0.8425 0.02121 0.01559 -0.0502 1.0000 0.0101
-9.250 -0.8190 0.02048 0.01479 -0.0499 1.0000 0.0103
-9.000 -0.7954 0.01977 0.01401 -0.0496 1.0000 0.0106
-8.750 -0.7719 0.01905 0.01321 -0.0493 1.0000 0.0109
-8.500 -0.7486 0.01830 0.01237 -0.0489 1.0000 0.0112
-8.250 -0.7255 0.01752 0.01148 -0.0483 1.0000 0.0117
-8.000 -0.7026 0.01676 0.01059 -0.0477 1.0000 0.0121
-7.750 -0.6796 0.01620 0.01000 -0.0471 1.0000 0.0124
-7.500 -0.6515 0.01576 0.00954 -0.0475 0.9986 0.0129
-7.250 -0.6194 0.01525 0.00899 -0.0487 0.9961 0.0134
-7.000 -0.5870 0.01469 0.00835 -0.0500 0.9939 0.0141
-6.750 -0.5553 0.01413 0.00771 -0.0510 0.9905 0.0148
-6.500 -0.5231 0.01366 0.00724 -0.0522 0.9872 0.0154
-6.250 -0.4902 0.01325 0.00680 -0.0535 0.9843 0.0162
-6.000 -0.4595 0.01284 0.00635 -0.0542 0.9795 0.0171
-5.750 -0.4275 0.01244 0.00593 -0.0553 0.9755 0.0181
-5.500 -0.3957 0.01211 0.00560 -0.0563 0.9715 0.0193
-5.250 -0.3651 0.01180 0.00525 -0.0569 0.9658 0.0205
-5.000 -0.3338 0.01140 0.00485 -0.0578 0.9609 0.0217
-4.750 -0.3042 0.01108 0.00453 -0.0582 0.9547 0.0230
-4.500 -0.2745 0.01079 0.00421 -0.0585 0.9484 0.0240
-4.250 -0.2453 0.01046 0.00388 -0.0588 0.9426 0.0252
-4.000 -0.2167 0.01022 0.00363 -0.0589 0.9355 0.0269
-3.750 -0.1881 0.00997 0.00337 -0.0590 0.9292 0.0288
-3.500 -0.1597 0.00975 0.00315 -0.0591 0.9222 0.0307
-3.250 -0.1313 0.00955 0.00294 -0.0590 0.9156 0.0329
-3.000 -0.1029 0.00936 0.00276 -0.0591 0.9095 0.0372
-2.750 -0.0744 0.00914 0.00259 -0.0591 0.9025 0.0473
-2.500 -0.0466 0.00892 0.00241 -0.0590 0.8939 0.0663
-2.250 -0.0186 0.00862 0.00225 -0.0590 0.8825 0.1080
-2.000 0.0096 0.00819 0.00206 -0.0592 0.8719 0.1852
-1.750 0.0382 0.00748 0.00184 -0.0597 0.8619 0.3348
-1.500 0.0669 0.00689 0.00175 -0.0602 0.8534 0.4838
-1.250 0.0947 0.00675 0.00180 -0.0600 0.8408 0.5561
-1.000 0.1220 0.00676 0.00184 -0.0595 0.8189 0.5948
-0.750 0.1491 0.00685 0.00185 -0.0589 0.7893 0.6176
-0.500 0.1766 0.00694 0.00184 -0.0585 0.7577 0.6299
-0.250 0.2043 0.00705 0.00180 -0.0582 0.7215 0.6356
0.000 0.2317 0.00722 0.00177 -0.0579 0.6710 0.6398
0.250 0.2569 0.00771 0.00180 -0.0572 0.5587 0.6437
0.500 0.2813 0.00852 0.00198 -0.0568 0.4039 0.6479
0.750 0.3074 0.00911 0.00214 -0.0566 0.2963 0.6523
1.000 0.3344 0.00954 0.00226 -0.0566 0.2271 0.6565
1.250 0.3617 0.00986 0.00239 -0.0565 0.1791 0.6602
1.500 0.3893 0.01011 0.00251 -0.0564 0.1516 0.6642
1.750 0.4173 0.01031 0.00263 -0.0564 0.1363 0.6683
2.000 0.4453 0.01049 0.00275 -0.0563 0.1263 0.6725
2.250 0.4734 0.01065 0.00288 -0.0563 0.1193 0.6762
2.500 0.5013 0.01079 0.00301 -0.0562 0.1141 0.6798
2.750 0.5291 0.01098 0.00317 -0.0561 0.1086 0.6837
3.000 0.5571 0.01113 0.00332 -0.0561 0.1051 0.6880
3.250 0.5850 0.01129 0.00348 -0.0560 0.1014 0.6921
3.500 0.6126 0.01147 0.00366 -0.0559 0.0974 0.6957
3.750 0.6402 0.01165 0.00384 -0.0558 0.0935 0.6999
4.000 0.6679 0.01181 0.00401 -0.0557 0.0888 0.7046
4.250 0.6953 0.01203 0.00419 -0.0556 0.0836 0.7091
4.500 0.7228 0.01218 0.00437 -0.0555 0.0794 0.7133
4.750 0.7500 0.01239 0.00457 -0.0553 0.0748 0.7180
5.000 0.7773 0.01258 0.00478 -0.0552 0.0706 0.7234
5.250 0.8043 0.01281 0.00499 -0.0550 0.0660 0.7289
5.500 0.8313 0.01301 0.00524 -0.0548 0.0618 0.7348
5.750 0.8580 0.01327 0.00549 -0.0546 0.0578 0.7412
6.000 0.8846 0.01352 0.00577 -0.0543 0.0539 0.7475
6.250 0.9110 0.01380 0.00607 -0.0541 0.0503 0.7550
6.750 0.9631 0.01440 0.00674 -0.0534 0.0436 0.7736
7.000 0.9886 0.01474 0.00712 -0.0530 0.0408 0.7852
7.250 1.0142 0.01504 0.00750 -0.0526 0.0384 0.7993
7.500 1.0390 0.01538 0.00790 -0.0521 0.0362 0.8180
7.750 1.0628 0.01566 0.00832 -0.0513 0.0344 0.8491
8.000 1.0832 0.01578 0.00865 -0.0496 0.0328 1.0000
8.250 1.1082 0.01627 0.00913 -0.0492 0.0314 1.0000
8.500 1.1334 0.01671 0.00963 -0.0489 0.0303 1.0000
8.750 1.1582 0.01719 0.01013 -0.0485 0.0291 1.0000
9.000 1.1826 0.01771 0.01067 -0.0480 0.0281 1.0000
9.250 1.2065 0.01829 0.01127 -0.0475 0.0273 1.0000
9.500 1.2304 0.01883 0.01187 -0.0469 0.0267 1.0000
9.750 1.2538 0.01940 0.01251 -0.0463 0.0261 1.0000
10.000 1.2769 0.02000 0.01317 -0.0457 0.0255 1.0000
10.250 1.2995 0.02063 0.01385 -0.0450 0.0250 1.0000
10.500 1.3213 0.02132 0.01459 -0.0443 0.0246 1.0000
10.750 1.3421 0.02211 0.01542 -0.0434 0.0242 1.0000
11.000 1.3623 0.02292 0.01630 -0.0425 0.0238 1.0000
11.250 1.3827 0.02367 0.01715 -0.0415 0.0235 1.0000
11.500 1.4023 0.02447 0.01804 -0.0405 0.0232 1.0000
11.750 1.4211 0.02530 0.01897 -0.0394 0.0229 1.0000
12.000 1.4391 0.02616 0.01992 -0.0382 0.0225 1.0000
12.250 1.4562 0.02705 0.02091 -0.0369 0.0222 1.0000
12.500 1.4720 0.02799 0.02194 -0.0355 0.0219 1.0000
12.750 1.4863 0.02900 0.02304 -0.0340 0.0217 1.0000
13.000 1.4985 0.03006 0.02420 -0.0321 0.0215 1.0000
13.250 1.5064 0.03118 0.02541 -0.0297 0.0213 1.0000
13.500 1.5125 0.03245 0.02678 -0.0272 0.0211 1.0000
13.750 1.5167 0.03392 0.02834 -0.0249 0.0210 1.0000
14.000 1.5188 0.03562 0.03015 -0.0226 0.0208 1.0000
14.250 1.5196 0.03755 0.03218 -0.0206 0.0207 1.0000
14.500 1.5216 0.03950 0.03430 -0.0191 0.0206 1.0000
14.750 1.5218 0.04173 0.03668 -0.0178 0.0205 1.0000
15.000 1.5201 0.04428 0.03939 -0.0168 0.0204 1.0000
15.250 1.5164 0.04722 0.04250 -0.0163 0.0203 1.0000
15.500 1.5101 0.05066 0.04611 -0.0163 0.0202 1.0000
15.750 1.5013 0.05470 0.05032 -0.0169 0.0201 1.0000
16.000 1.4893 0.05957 0.05536 -0.0185 0.0201 1.0000
16.250 1.4732 0.06557 0.06156 -0.0213 0.0200 1.0000
16.500 1.4522 0.07323 0.06942 -0.0257 0.0200 1.0000
16.750 1.4236 0.08322 0.07964 -0.0321 0.0200 1.0000
17.000 1.3855 0.09577 0.09242 -0.0401 0.0201 1.0000
17.250 1.3374 0.11029 0.10715 -0.0487 0.0201 1.0000
17.500 1.2840 0.12594 0.12300 -0.0579 0.0202 1.0000
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