RAE(NPL) 5212 AIRFOIL (rae5212-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: RAE(NPL) 5212 AIRFOIL (rae5212-il) Reynolds number: 200,000 Max Cl/Cd: 48.24 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae5212-il-200000-n5.txt Download as CSV file: xf-rae5212-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: RAE(NPL) 5212 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5495 0.09136 0.08735 -0.0452 1.0000 0.0190
-11.500 -0.5995 0.07338 0.06931 -0.0560 1.0000 0.0185
-11.250 -0.6419 0.06320 0.05898 -0.0625 1.0000 0.0182
-11.000 -0.6747 0.05692 0.05253 -0.0650 1.0000 0.0181
-10.750 -0.7029 0.05241 0.04787 -0.0652 1.0000 0.0181
-10.500 -0.7307 0.04915 0.04446 -0.0631 1.0000 0.0180
-10.250 -0.7569 0.04674 0.04192 -0.0589 1.0000 0.0180
-10.000 -0.7756 0.04367 0.03861 -0.0553 1.0000 0.0181
-9.750 -0.7896 0.04052 0.03514 -0.0518 1.0000 0.0184
-9.500 -0.7976 0.03748 0.03171 -0.0485 1.0000 0.0188
-9.250 -0.8017 0.03440 0.02811 -0.0453 1.0000 0.0194
-9.000 -0.7766 0.03263 0.02619 -0.0468 0.9969 0.0199
-8.750 -0.7491 0.03112 0.02453 -0.0484 0.9940 0.0205
-8.500 -0.7237 0.02939 0.02257 -0.0493 0.9903 0.0211
-8.250 -0.6964 0.02760 0.02050 -0.0504 0.9870 0.0217
-8.000 -0.6673 0.02590 0.01852 -0.0515 0.9844 0.0225
-7.750 -0.6408 0.02447 0.01680 -0.0519 0.9806 0.0234
-7.500 -0.6130 0.02341 0.01573 -0.0527 0.9768 0.0243
-7.250 -0.5820 0.02262 0.01488 -0.0540 0.9738 0.0255
-7.000 -0.5524 0.02167 0.01381 -0.0548 0.9707 0.0268
-6.750 -0.5268 0.02074 0.01276 -0.0547 0.9656 0.0278
-6.500 -0.4976 0.01980 0.01180 -0.0555 0.9621 0.0289
-6.250 -0.4657 0.01906 0.01106 -0.0568 0.9595 0.0303
-6.000 -0.4414 0.01848 0.01044 -0.0564 0.9533 0.0322
-5.750 -0.4121 0.01778 0.00969 -0.0571 0.9492 0.0343
-5.500 -0.3804 0.01714 0.00906 -0.0583 0.9464 0.0365
-5.250 -0.3539 0.01661 0.00849 -0.0583 0.9412 0.0391
-5.000 -0.3263 0.01603 0.00791 -0.0587 0.9361 0.0425
-4.750 -0.2940 0.01552 0.00736 -0.0598 0.9329 0.0466
-4.500 -0.2605 0.01495 0.00681 -0.0613 0.9306 0.0525
-4.250 -0.2375 0.01456 0.00640 -0.0605 0.9232 0.0596
-4.000 -0.2063 0.01406 0.00594 -0.0614 0.9193 0.0722
-3.750 -0.1737 0.01348 0.00550 -0.0627 0.9164 0.1015
-3.500 -0.1496 0.01278 0.00511 -0.0625 0.9099 0.1723
-3.250 -0.1253 0.01151 0.00464 -0.0628 0.9048 0.3607
-3.000 -0.0960 0.01096 0.00468 -0.0632 0.9014 0.5078
-2.750 -0.0684 0.01095 0.00472 -0.0629 0.8954 0.5549
-2.500 -0.0383 0.01098 0.00475 -0.0631 0.8903 0.5849
-2.250 -0.0059 0.01108 0.00488 -0.0636 0.8865 0.6143
-2.000 0.0236 0.01123 0.00502 -0.0635 0.8814 0.6366
-1.750 0.0522 0.01126 0.00505 -0.0634 0.8751 0.6469
-1.500 0.0851 0.01119 0.00489 -0.0643 0.8707 0.6521
-1.250 0.1158 0.01113 0.00480 -0.0647 0.8654 0.6557
-1.000 0.1443 0.01110 0.00475 -0.0647 0.8587 0.6598
-0.750 0.1766 0.01104 0.00463 -0.0655 0.8539 0.6642
-0.500 0.2053 0.01102 0.00457 -0.0656 0.8473 0.6683
-0.250 0.2343 0.01098 0.00454 -0.0657 0.8406 0.6716
0.000 0.2652 0.01093 0.00446 -0.0661 0.8336 0.6753
0.250 0.2929 0.01091 0.00442 -0.0659 0.8239 0.6794
0.500 0.3218 0.01088 0.00434 -0.0659 0.8133 0.6836
0.750 0.3498 0.01079 0.00424 -0.0655 0.7976 0.6868
1.000 0.3770 0.01074 0.00414 -0.0650 0.7790 0.6904
1.250 0.4042 0.01069 0.00401 -0.0644 0.7556 0.6944
1.500 0.4297 0.01070 0.00389 -0.0635 0.7248 0.6986
1.750 0.4549 0.01073 0.00383 -0.0626 0.6938 0.7022
2.000 0.4801 0.01079 0.00383 -0.0618 0.6667 0.7060
2.250 0.5050 0.01088 0.00385 -0.0610 0.6361 0.7102
2.500 0.5286 0.01105 0.00386 -0.0599 0.5921 0.7147
2.750 0.5485 0.01137 0.00390 -0.0582 0.5274 0.7186
3.000 0.5646 0.01192 0.00407 -0.0558 0.4444 0.7227
3.250 0.5805 0.01257 0.00433 -0.0536 0.3642 0.7272
3.500 0.5977 0.01324 0.00463 -0.0518 0.2915 0.7321
3.750 0.6161 0.01381 0.00496 -0.0502 0.2329 0.7365
4.000 0.6360 0.01433 0.00528 -0.0489 0.1880 0.7415
4.250 0.6570 0.01482 0.00560 -0.0479 0.1543 0.7468
4.500 0.6785 0.01525 0.00593 -0.0468 0.1326 0.7517
4.750 0.7005 0.01563 0.00629 -0.0458 0.1191 0.7573
5.000 0.7228 0.01600 0.00664 -0.0449 0.1098 0.7641
5.250 0.7441 0.01637 0.00701 -0.0437 0.1028 0.7707
5.500 0.7658 0.01673 0.00740 -0.0427 0.0982 0.7786
5.750 0.7874 0.01706 0.00782 -0.0416 0.0944 0.7868
6.000 0.8085 0.01745 0.00823 -0.0405 0.0909 0.7966
6.250 0.8284 0.01794 0.00873 -0.0392 0.0877 0.8081
6.500 0.8501 0.01827 0.00919 -0.0381 0.0854 0.8231
7.000 0.8942 0.01898 0.01019 -0.0361 0.0809 0.8946
7.250 0.9224 0.01951 0.01078 -0.0367 0.0787 1.0000
7.500 0.9424 0.02016 0.01140 -0.0356 0.0767 1.0000
7.750 0.9627 0.02086 0.01208 -0.0346 0.0749 1.0000
8.000 0.9841 0.02141 0.01270 -0.0337 0.0734 1.0000
8.250 1.0048 0.02202 0.01337 -0.0327 0.0719 1.0000
8.500 1.0253 0.02266 0.01407 -0.0317 0.0704 1.0000
8.750 1.0455 0.02333 0.01477 -0.0307 0.0690 1.0000
9.000 1.0654 0.02403 0.01551 -0.0296 0.0677 1.0000
9.250 1.0848 0.02476 0.01627 -0.0286 0.0663 1.0000
9.500 1.1051 0.02572 0.01721 -0.0278 0.0648 1.0000
9.750 1.1260 0.02666 0.01821 -0.0270 0.0636 1.0000
10.000 1.1454 0.02744 0.01914 -0.0259 0.0626 1.0000
10.250 1.1645 0.02831 0.02014 -0.0249 0.0615 1.0000
10.500 1.1827 0.02920 0.02115 -0.0237 0.0602 1.0000
10.750 1.1996 0.03006 0.02212 -0.0224 0.0589 1.0000
11.000 1.2155 0.03092 0.02307 -0.0210 0.0577 1.0000
11.250 1.2309 0.03181 0.02403 -0.0196 0.0567 1.0000
11.500 1.2456 0.03273 0.02499 -0.0182 0.0556 1.0000
11.750 1.2618 0.03404 0.02630 -0.0172 0.0543 1.0000
12.000 1.2703 0.03493 0.02743 -0.0150 0.0532 1.0000
12.250 1.2792 0.03600 0.02872 -0.0130 0.0518 1.0000
12.500 1.2878 0.03711 0.03000 -0.0111 0.0505 1.0000
12.750 1.2962 0.03827 0.03130 -0.0094 0.0494 1.0000
13.000 1.3040 0.03939 0.03252 -0.0077 0.0484 1.0000
13.250 1.3115 0.04053 0.03373 -0.0062 0.0475 1.0000
13.500 1.3186 0.04175 0.03500 -0.0048 0.0467 1.0000
13.750 1.3246 0.04334 0.03666 -0.0035 0.0459 1.0000
14.000 1.3238 0.04544 0.03907 -0.0019 0.0449 1.0000
14.250 1.3228 0.04767 0.04155 -0.0007 0.0438 1.0000
14.500 1.3217 0.04998 0.04405 0.0003 0.0428 1.0000
14.750 1.3207 0.05229 0.04653 0.0010 0.0419 1.0000
15.000 1.3196 0.05470 0.04908 0.0014 0.0412 1.0000
15.250 1.3201 0.05694 0.05141 0.0015 0.0404 1.0000
15.500 1.3201 0.05935 0.05389 0.0014 0.0397 1.0000
15.750 1.3184 0.06214 0.05677 0.0011 0.0392 1.0000
16.000 1.3059 0.06666 0.06152 0.0000 0.0385 1.0000
16.250 1.2872 0.07245 0.06759 -0.0020 0.0380 1.0000
16.500 1.2647 0.07931 0.07473 -0.0052 0.0375 1.0000
16.750 1.2364 0.08786 0.08354 -0.0099 0.0371 1.0000
17.000 1.1924 0.10047 0.09644 -0.0178 0.0372 1.0000
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