RAE 5215 AIRFOIL (rae5215-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 5215 AIRFOIL (rae5215-il) Reynolds number: 500,000 Max Cl/Cd: 67.4 at α=6.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae5215-il-500000.txt Download as CSV file: xf-rae5215-il-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.750 -0.5755 0.11468 0.11219 -0.0023 1.0000 0.0227
-10.500 -0.5769 0.10918 0.10670 -0.0054 1.0000 0.0235
-10.250 -0.6053 0.09289 0.09045 -0.0182 1.0000 0.0242
-10.000 -0.6019 0.09051 0.08808 -0.0181 1.0000 0.0244
-9.750 -0.6000 0.08685 0.08444 -0.0197 1.0000 0.0245
-9.500 -0.6013 0.08169 0.07930 -0.0231 1.0000 0.0246
-9.250 -0.6225 0.06946 0.06702 -0.0351 1.0000 0.0246
-9.000 -0.6462 0.06190 0.05933 -0.0428 1.0000 0.0246
-8.750 -0.6490 0.05764 0.05496 -0.0456 1.0000 0.0248
-8.500 -0.6465 0.05403 0.05125 -0.0471 1.0000 0.0250
-8.250 -0.6950 0.03193 0.02747 -0.0496 1.0000 0.0175
-8.000 -0.6808 0.02871 0.02401 -0.0490 1.0000 0.0173
-7.750 -0.6654 0.02539 0.02031 -0.0482 1.0000 0.0171
-7.500 -0.6478 0.02257 0.01704 -0.0472 1.0000 0.0173
-7.250 -0.6289 0.02050 0.01461 -0.0461 1.0000 0.0178
-7.000 -0.6096 0.01930 0.01339 -0.0450 1.0000 0.0183
-6.750 -0.5903 0.01861 0.01268 -0.0438 1.0000 0.0188
-6.500 -0.5710 0.01779 0.01175 -0.0425 1.0000 0.0196
-6.250 -0.5425 0.01691 0.01063 -0.0428 0.9991 0.0206
-6.000 -0.5095 0.01570 0.00943 -0.0443 0.9974 0.0217
-5.750 -0.4747 0.01503 0.00873 -0.0460 0.9956 0.0229
-5.500 -0.4392 0.01445 0.00801 -0.0476 0.9939 0.0241
-5.250 -0.4062 0.01353 0.00717 -0.0491 0.9914 0.0257
-5.000 -0.3712 0.01320 0.00678 -0.0507 0.9890 0.0278
-4.750 -0.3364 0.01248 0.00612 -0.0525 0.9870 0.0299
-4.500 -0.3001 0.01207 0.00568 -0.0544 0.9854 0.0320
-4.250 -0.2647 0.01141 0.00506 -0.0562 0.9834 0.0339
-4.000 -0.2302 0.01101 0.00466 -0.0577 0.9801 0.0360
-3.750 -0.1946 0.01056 0.00423 -0.0595 0.9776 0.0386
-3.500 -0.1589 0.01027 0.00394 -0.0612 0.9752 0.0420
-3.250 -0.1230 0.00985 0.00356 -0.0629 0.9730 0.0461
-3.000 -0.0920 0.00952 0.00327 -0.0636 0.9673 0.0532
-2.750 -0.0589 0.00878 0.00287 -0.0649 0.9629 0.1262
-2.500 -0.0283 0.00718 0.00243 -0.0667 0.9568 0.4339
-2.250 -0.0004 0.00685 0.00243 -0.0665 0.9477 0.5401
-2.000 0.0267 0.00680 0.00243 -0.0659 0.9383 0.5746
-1.750 0.0539 0.00680 0.00244 -0.0653 0.9302 0.5976
-1.500 0.0812 0.00683 0.00248 -0.0648 0.9217 0.6170
-1.250 0.1071 0.00689 0.00251 -0.0638 0.9111 0.6365
-1.000 0.1319 0.00696 0.00257 -0.0624 0.8951 0.6555
-0.750 0.1570 0.00702 0.00261 -0.0612 0.8774 0.6699
-0.500 0.1836 0.00704 0.00259 -0.0604 0.8604 0.6790
-0.250 0.2111 0.00703 0.00255 -0.0600 0.8456 0.6839
0.000 0.2392 0.00704 0.00252 -0.0597 0.8322 0.6887
0.250 0.2673 0.00707 0.00247 -0.0594 0.8164 0.6931
0.500 0.2949 0.00705 0.00243 -0.0590 0.7970 0.6973
0.750 0.3225 0.00708 0.00241 -0.0587 0.7734 0.7016
1.000 0.3500 0.00716 0.00238 -0.0582 0.7391 0.7063
1.250 0.3757 0.00743 0.00233 -0.0575 0.6577 0.7107
1.500 0.3954 0.00867 0.00254 -0.0561 0.4151 0.7148
1.750 0.4182 0.00977 0.00286 -0.0556 0.2303 0.7193
2.250 0.4722 0.01056 0.00322 -0.0554 0.1512 0.7286
2.500 0.4996 0.01075 0.00338 -0.0553 0.1411 0.7331
2.750 0.5272 0.01096 0.00358 -0.0551 0.1336 0.7378
3.000 0.5550 0.01117 0.00376 -0.0551 0.1276 0.7429
3.250 0.5819 0.01148 0.00404 -0.0549 0.1213 0.7478
3.500 0.6096 0.01160 0.00422 -0.0547 0.1174 0.7531
3.750 0.6371 0.01181 0.00441 -0.0546 0.1122 0.7587
4.000 0.6639 0.01211 0.00470 -0.0544 0.1064 0.7644
4.250 0.6915 0.01219 0.00483 -0.0543 0.1015 0.7706
4.500 0.7183 0.01248 0.00508 -0.0541 0.0961 0.7776
4.750 0.7455 0.01264 0.00530 -0.0539 0.0918 0.7843
5.000 0.7728 0.01279 0.00547 -0.0538 0.0871 0.7924
5.250 0.7992 0.01305 0.00575 -0.0535 0.0824 0.8013
5.500 0.8263 0.01318 0.00593 -0.0533 0.0780 0.8126
5.750 0.8520 0.01344 0.00622 -0.0529 0.0735 0.8262
6.000 0.8781 0.01354 0.00642 -0.0524 0.0692 0.8449
6.250 0.9012 0.01370 0.00669 -0.0514 0.0649 0.8809
6.500 0.9247 0.01372 0.00683 -0.0503 0.0606 1.0000
6.750 0.9515 0.01412 0.00720 -0.0502 0.0562 1.0000
7.000 0.9772 0.01463 0.00764 -0.0500 0.0520 1.0000
7.250 1.0037 0.01501 0.00805 -0.0498 0.0486 1.0000
7.500 1.0283 0.01565 0.00866 -0.0493 0.0457 1.0000
7.750 1.0539 0.01611 0.00916 -0.0490 0.0433 1.0000
8.000 1.0784 0.01671 0.00974 -0.0485 0.0414 1.0000
8.250 1.1022 0.01741 0.01047 -0.0479 0.0398 1.0000
8.500 1.1270 0.01793 0.01105 -0.0475 0.0383 1.0000
8.750 1.1510 0.01852 0.01165 -0.0469 0.0371 1.0000
9.000 1.1731 0.01941 0.01252 -0.0462 0.0360 1.0000
9.250 1.1960 0.02019 0.01338 -0.0455 0.0353 1.0000
9.500 1.2191 0.02089 0.01417 -0.0448 0.0345 1.0000
9.750 1.2416 0.02164 0.01500 -0.0441 0.0338 1.0000
10.000 1.2637 0.02241 0.01583 -0.0433 0.0331 1.0000
10.250 1.2851 0.02323 0.01669 -0.0425 0.0325 1.0000
10.500 1.3055 0.02420 0.01769 -0.0416 0.0320 1.0000
10.750 1.3234 0.02571 0.01925 -0.0404 0.0314 1.0000
11.000 1.3434 0.02658 0.02028 -0.0394 0.0310 1.0000
11.250 1.3622 0.02759 0.02144 -0.0383 0.0306 1.0000
11.500 1.3798 0.02874 0.02273 -0.0371 0.0302 1.0000
11.750 1.3962 0.02997 0.02409 -0.0357 0.0298 1.0000
12.000 1.4112 0.03125 0.02551 -0.0342 0.0295 1.0000
12.250 1.4249 0.03257 0.02697 -0.0327 0.0291 1.0000
12.500 1.4370 0.03394 0.02847 -0.0309 0.0289 1.0000
12.750 1.4472 0.03537 0.03002 -0.0291 0.0286 1.0000
13.000 1.4534 0.03683 0.03159 -0.0266 0.0284 1.0000
13.250 1.4569 0.03845 0.03332 -0.0240 0.0282 1.0000
13.500 1.4584 0.04032 0.03531 -0.0215 0.0280 1.0000
13.750 1.4571 0.04256 0.03768 -0.0192 0.0279 1.0000
14.000 1.4517 0.04530 0.04058 -0.0171 0.0277 1.0000
14.250 1.4414 0.04864 0.04412 -0.0152 0.0276 1.0000
14.500 1.4266 0.05260 0.04830 -0.0140 0.0275 1.0000
14.750 1.4111 0.05672 0.05263 -0.0136 0.0275 1.0000
15.000 1.3930 0.06157 0.05771 -0.0144 0.0275 1.0000
15.250 1.3714 0.06749 0.06385 -0.0164 0.0275 1.0000
15.500 1.3456 0.07483 0.07141 -0.0202 0.0275 1.0000
16.000 1.2769 0.09699 0.09409 -0.0363 0.0277 1.0000
16.250 0.6735 0.17843 0.17629 -0.0654 0.0363 1.0000
16.500 0.6820 0.18037 0.17825 -0.0654 0.0361 1.0000
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