RAE(NPL) 5213 AIRFOIL (rae5213-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE(NPL) 5213 AIRFOIL (rae5213-il) Reynolds number: 500,000 Max Cl/Cd: 65.91 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae5213-il-500000.txt Download as CSV file: xf-rae5213-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: RAE(NPL) 5213 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 -0.5413 0.09725 0.09470 -0.0245 1.0000 0.0235
-10.500 -0.5380 0.09436 0.09183 -0.0249 1.0000 0.0236
-10.250 -0.5365 0.09070 0.08819 -0.0263 1.0000 0.0237
-10.000 -0.5361 0.08672 0.08423 -0.0281 1.0000 0.0239
-9.750 -0.5366 0.08266 0.08020 -0.0300 1.0000 0.0241
-9.500 -0.5415 0.07717 0.07473 -0.0335 1.0000 0.0242
-9.250 -0.5715 0.06517 0.06268 -0.0445 1.0000 0.0241
-9.000 -0.6019 0.05933 0.05677 -0.0481 1.0000 0.0241
-8.750 -0.6172 0.05507 0.05238 -0.0491 1.0000 0.0242
-8.500 -0.7016 0.03321 0.02903 -0.0475 1.0000 0.0168
-8.250 -0.6959 0.02965 0.02515 -0.0458 1.0000 0.0167
-8.000 -0.6881 0.02615 0.02117 -0.0439 1.0000 0.0168
-7.750 -0.6766 0.02323 0.01781 -0.0421 1.0000 0.0171
-7.500 -0.6598 0.02183 0.01634 -0.0408 1.0000 0.0175
-7.250 -0.6415 0.02113 0.01563 -0.0395 1.0000 0.0179
-7.000 -0.6236 0.02007 0.01445 -0.0380 1.0000 0.0184
-6.750 -0.6046 0.01888 0.01306 -0.0367 0.9999 0.0191
-6.500 -0.5694 0.01778 0.01162 -0.0383 0.9977 0.0200
-6.250 -0.5364 0.01640 0.01027 -0.0399 0.9956 0.0210
-6.000 -0.5015 0.01570 0.00953 -0.0416 0.9933 0.0222
-5.750 -0.4672 0.01493 0.00861 -0.0430 0.9903 0.0237
-5.500 -0.4325 0.01423 0.00798 -0.0448 0.9877 0.0252
-5.250 -0.3954 0.01381 0.00746 -0.0467 0.9856 0.0270
-5.000 -0.3624 0.01298 0.00671 -0.0481 0.9821 0.0289
-4.750 -0.3275 0.01245 0.00615 -0.0496 0.9786 0.0306
-4.500 -0.2914 0.01174 0.00546 -0.0515 0.9761 0.0322
-4.250 -0.2533 0.01130 0.00504 -0.0537 0.9743 0.0345
-4.000 -0.2210 0.01083 0.00456 -0.0547 0.9688 0.0366
-3.750 -0.1852 0.01039 0.00415 -0.0564 0.9651 0.0389
-3.500 -0.1487 0.00998 0.00375 -0.0581 0.9621 0.0422
-3.250 -0.1190 0.00966 0.00344 -0.0584 0.9544 0.0460
-3.000 -0.0852 0.00929 0.00309 -0.0595 0.9495 0.0538
-2.750 -0.0575 0.00857 0.00269 -0.0596 0.9401 0.1198
-2.500 -0.0319 0.00705 0.00222 -0.0601 0.9313 0.4033
-2.250 -0.0057 0.00659 0.00218 -0.0597 0.9206 0.5322
-2.000 0.0216 0.00652 0.00219 -0.0592 0.9098 0.5722
-1.750 0.0494 0.00651 0.00217 -0.0587 0.8982 0.5963
-1.500 0.0765 0.00653 0.00215 -0.0580 0.8847 0.6143
-1.250 0.1034 0.00660 0.00221 -0.0574 0.8717 0.6346
-1.000 0.1305 0.00671 0.00231 -0.0568 0.8599 0.6539
-0.750 0.1570 0.00680 0.00239 -0.0559 0.8455 0.6690
-0.500 0.1835 0.00684 0.00237 -0.0552 0.8265 0.6783
-0.250 0.2100 0.00686 0.00231 -0.0545 0.8044 0.6832
0.000 0.2371 0.00690 0.00226 -0.0540 0.7840 0.6880
0.250 0.2645 0.00696 0.00223 -0.0536 0.7652 0.6924
0.500 0.2915 0.00697 0.00220 -0.0531 0.7463 0.6966
0.750 0.3188 0.00702 0.00220 -0.0527 0.7281 0.7009
1.000 0.3459 0.00710 0.00220 -0.0523 0.7063 0.7056
1.250 0.3729 0.00720 0.00221 -0.0519 0.6806 0.7101
1.500 0.3991 0.00728 0.00221 -0.0513 0.6467 0.7143
1.750 0.4244 0.00748 0.00224 -0.0505 0.5962 0.7188
2.000 0.4480 0.00788 0.00230 -0.0496 0.5121 0.7236
2.250 0.4694 0.00864 0.00250 -0.0485 0.3858 0.7281
2.500 0.4897 0.00960 0.00282 -0.0474 0.2344 0.7325
2.750 0.5131 0.01026 0.00310 -0.0468 0.1558 0.7373
3.000 0.5390 0.01062 0.00333 -0.0464 0.1334 0.7424
3.250 0.5654 0.01085 0.00354 -0.0461 0.1224 0.7473
3.500 0.5915 0.01111 0.00378 -0.0457 0.1143 0.7526
3.750 0.6180 0.01134 0.00399 -0.0454 0.1080 0.7581
4.000 0.6439 0.01164 0.00428 -0.0450 0.1014 0.7639
4.250 0.6702 0.01181 0.00448 -0.0446 0.0960 0.7701
4.500 0.6952 0.01221 0.00484 -0.0441 0.0902 0.7771
4.750 0.7219 0.01233 0.00504 -0.0438 0.0864 0.7840
5.000 0.7477 0.01256 0.00528 -0.0434 0.0821 0.7921
5.250 0.7726 0.01290 0.00564 -0.0428 0.0781 0.8012
5.500 0.7987 0.01305 0.00586 -0.0424 0.0744 0.8127
5.750 0.8231 0.01332 0.00616 -0.0418 0.0705 0.8268
6.000 0.8479 0.01347 0.00642 -0.0411 0.0670 0.8467
6.250 0.8699 0.01349 0.00659 -0.0397 0.0634 0.8905
6.500 0.9005 0.01373 0.00692 -0.0404 0.0593 1.0000
6.750 0.9267 0.01406 0.00720 -0.0402 0.0556 1.0000
7.000 0.9519 0.01448 0.00763 -0.0398 0.0519 1.0000
7.250 0.9765 0.01493 0.00803 -0.0394 0.0488 1.0000
7.500 1.0008 0.01543 0.00856 -0.0388 0.0460 1.0000
7.750 1.0252 0.01588 0.00899 -0.0383 0.0436 1.0000
8.000 1.0478 0.01655 0.00966 -0.0375 0.0417 1.0000
8.250 1.0717 0.01704 0.01020 -0.0369 0.0400 1.0000
8.500 1.0950 0.01758 0.01075 -0.0362 0.0386 1.0000
8.750 1.1155 0.01850 0.01163 -0.0353 0.0373 1.0000
9.000 1.1383 0.01909 0.01231 -0.0345 0.0365 1.0000
9.250 1.1606 0.01975 0.01305 -0.0337 0.0356 1.0000
9.500 1.1824 0.02042 0.01377 -0.0329 0.0347 1.0000
9.750 1.2037 0.02113 0.01450 -0.0320 0.0340 1.0000
10.000 1.2241 0.02193 0.01531 -0.0311 0.0333 1.0000
10.250 1.2425 0.02316 0.01658 -0.0300 0.0326 1.0000
10.500 1.2627 0.02393 0.01748 -0.0290 0.0321 1.0000
10.750 1.2819 0.02484 0.01850 -0.0279 0.0316 1.0000
11.000 1.3003 0.02583 0.01959 -0.0268 0.0312 1.0000
11.250 1.3178 0.02684 0.02071 -0.0256 0.0307 1.0000
11.500 1.3344 0.02788 0.02185 -0.0243 0.0303 1.0000
11.750 1.3500 0.02895 0.02300 -0.0229 0.0300 1.0000
12.000 1.3645 0.03006 0.02419 -0.0214 0.0296 1.0000
12.250 1.3766 0.03128 0.02549 -0.0197 0.0294 1.0000
12.500 1.3866 0.03268 0.02696 -0.0177 0.0291 1.0000
12.750 1.3940 0.03461 0.02899 -0.0158 0.0288 1.0000
13.000 1.3964 0.03671 0.03127 -0.0134 0.0286 1.0000
13.250 1.3971 0.03844 0.03318 -0.0109 0.0285 1.0000
13.500 1.3950 0.04043 0.03538 -0.0086 0.0283 1.0000
13.750 1.3907 0.04277 0.03792 -0.0067 0.0282 1.0000
14.000 1.3834 0.04551 0.04088 -0.0052 0.0281 1.0000
14.250 1.3735 0.04876 0.04433 -0.0042 0.0281 1.0000
14.500 1.3603 0.05253 0.04832 -0.0040 0.0280 1.0000
14.750 1.3442 0.05703 0.05304 -0.0046 0.0279 1.0000
15.000 1.3245 0.06244 0.05867 -0.0062 0.0280 1.0000
15.250 1.2998 0.06911 0.06557 -0.0093 0.0280 1.0000
15.500 1.2707 0.07732 0.07401 -0.0142 0.0280 1.0000
15.750 1.2339 0.08812 0.08506 -0.0215 0.0281 1.0000
16.000 1.1781 0.10484 0.10205 -0.0335 0.0284 1.0000
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Polar data table (+)
Polar graphs
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