RAE 5214 AIRFOIL (rae5214-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: RAE 5214 AIRFOIL (rae5214-il) Reynolds number: 1,000,000 Max Cl/Cd: 83.26 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-rae5214-il-1000000.txt Download as CSV file: xf-rae5214-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: RAE 5214 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.500 -0.7964 0.06381 0.06174 -0.0404 1.0000 0.0097
-12.250 -0.7916 0.06021 0.05813 -0.0435 1.0000 0.0097
-12.000 -0.7898 0.05645 0.05434 -0.0468 1.0000 0.0098
-11.750 -0.7824 0.05420 0.05206 -0.0487 1.0000 0.0099
-11.500 -0.7764 0.05198 0.04983 -0.0505 1.0000 0.0099
-11.250 -0.9329 0.03067 0.02722 -0.0559 1.0000 0.0093
-11.000 -0.9317 0.02792 0.02419 -0.0545 1.0000 0.0093
-10.750 -0.9343 0.02409 0.01995 -0.0526 1.0000 0.0094
-10.500 -0.9246 0.02188 0.01749 -0.0511 1.0000 0.0095
-10.250 -0.9098 0.02044 0.01590 -0.0498 1.0000 0.0097
-10.000 -0.8920 0.01950 0.01488 -0.0486 1.0000 0.0098
-9.750 -0.8731 0.01876 0.01407 -0.0474 1.0000 0.0100
-9.500 -0.8542 0.01804 0.01327 -0.0462 1.0000 0.0102
-9.250 -0.8347 0.01744 0.01262 -0.0450 1.0000 0.0104
-9.000 -0.8157 0.01678 0.01188 -0.0436 1.0000 0.0107
-8.750 -0.7969 0.01611 0.01113 -0.0423 1.0000 0.0109
-8.500 -0.7768 0.01556 0.01050 -0.0410 0.9999 0.0113
-8.250 -0.7446 0.01480 0.00964 -0.0423 0.9986 0.0117
-8.000 -0.7120 0.01412 0.00893 -0.0438 0.9970 0.0123
-7.750 -0.6782 0.01382 0.00863 -0.0452 0.9956 0.0128
-7.500 -0.6444 0.01337 0.00813 -0.0467 0.9943 0.0134
-7.250 -0.6123 0.01306 0.00775 -0.0476 0.9921 0.0141
-7.000 -0.5804 0.01235 0.00703 -0.0488 0.9900 0.0148
-6.750 -0.5466 0.01208 0.00677 -0.0502 0.9882 0.0155
-6.500 -0.5124 0.01173 0.00638 -0.0516 0.9868 0.0163
-6.250 -0.4777 0.01139 0.00599 -0.0531 0.9856 0.0171
-6.000 -0.4448 0.01085 0.00547 -0.0544 0.9838 0.0181
-5.750 -0.4126 0.01053 0.00515 -0.0554 0.9807 0.0190
-5.500 -0.3788 0.01029 0.00488 -0.0566 0.9784 0.0200
-5.250 -0.3457 0.00973 0.00433 -0.0579 0.9759 0.0212
-5.000 -0.3137 0.00944 0.00404 -0.0588 0.9726 0.0224
-4.750 -0.2844 0.00922 0.00381 -0.0589 0.9664 0.0234
-4.500 -0.2539 0.00879 0.00338 -0.0595 0.9619 0.0249
-4.250 -0.2269 0.00857 0.00316 -0.0592 0.9541 0.0263
-4.000 -0.1977 0.00831 0.00288 -0.0594 0.9483 0.0278
-3.750 -0.1709 0.00808 0.00265 -0.0590 0.9398 0.0296
-3.500 -0.1427 0.00790 0.00245 -0.0588 0.9329 0.0310
-3.250 -0.1157 0.00768 0.00223 -0.0585 0.9242 0.0331
-3.000 -0.0881 0.00753 0.00206 -0.0582 0.9161 0.0361
-2.750 -0.0614 0.00733 0.00188 -0.0578 0.9042 0.0439
-2.500 -0.0351 0.00698 0.00168 -0.0574 0.8915 0.0865
-2.250 -0.0095 0.00639 0.00146 -0.0571 0.8781 0.2004
-2.000 0.0153 0.00558 0.00120 -0.0568 0.8636 0.3821
-1.750 0.0414 0.00516 0.00111 -0.0565 0.8502 0.4971
-1.500 0.0688 0.00505 0.00110 -0.0562 0.8380 0.5431
-1.250 0.0964 0.00504 0.00108 -0.0558 0.8234 0.5672
-1.000 0.1237 0.00505 0.00108 -0.0554 0.8046 0.5875
-0.750 0.1510 0.00510 0.00109 -0.0550 0.7852 0.6055
-0.500 0.1787 0.00516 0.00113 -0.0547 0.7690 0.6223
-0.250 0.2063 0.00524 0.00117 -0.0543 0.7518 0.6361
0.000 0.2336 0.00531 0.00120 -0.0539 0.7291 0.6460
0.250 0.2608 0.00543 0.00121 -0.0535 0.7027 0.6507
0.500 0.2878 0.00557 0.00122 -0.0531 0.6683 0.6545
0.750 0.3136 0.00581 0.00125 -0.0525 0.6073 0.6581
1.000 0.3370 0.00630 0.00134 -0.0516 0.5008 0.6622
1.250 0.3603 0.00694 0.00151 -0.0508 0.3809 0.6661
1.750 0.4096 0.00802 0.00185 -0.0497 0.2001 0.6736
2.000 0.4363 0.00824 0.00196 -0.0495 0.1708 0.6777
2.250 0.4633 0.00843 0.00208 -0.0492 0.1506 0.6818
2.500 0.4905 0.00862 0.00219 -0.0490 0.1336 0.6858
2.750 0.5177 0.00881 0.00231 -0.0487 0.1207 0.6897
3.000 0.5450 0.00899 0.00244 -0.0485 0.1112 0.6934
3.250 0.5720 0.00914 0.00257 -0.0483 0.1039 0.6977
3.500 0.5992 0.00929 0.00272 -0.0480 0.0979 0.7019
3.750 0.6263 0.00948 0.00286 -0.0478 0.0920 0.7062
4.000 0.6535 0.00965 0.00303 -0.0476 0.0875 0.7102
4.250 0.6806 0.00977 0.00317 -0.0473 0.0838 0.7149
4.500 0.7073 0.00998 0.00336 -0.0470 0.0790 0.7196
4.750 0.7345 0.01012 0.00352 -0.0468 0.0757 0.7247
5.000 0.7614 0.01029 0.00367 -0.0465 0.0715 0.7299
5.250 0.7880 0.01047 0.00386 -0.0462 0.0676 0.7355
5.500 0.8147 0.01064 0.00404 -0.0459 0.0638 0.7415
5.750 0.8411 0.01085 0.00425 -0.0456 0.0601 0.7477
6.000 0.8675 0.01103 0.00445 -0.0453 0.0566 0.7553
6.250 0.8936 0.01127 0.00470 -0.0449 0.0530 0.7635
6.500 0.9196 0.01149 0.00493 -0.0445 0.0494 0.7734
6.750 0.9453 0.01172 0.00521 -0.0441 0.0459 0.7847
7.000 0.9702 0.01203 0.00553 -0.0436 0.0420 0.7995
7.250 0.9953 0.01222 0.00581 -0.0430 0.0391 0.8218
7.500 1.0176 0.01241 0.00617 -0.0418 0.0365 0.8743
7.750 1.0449 0.01255 0.00647 -0.0417 0.0343 1.0000
8.000 1.0695 0.01301 0.00691 -0.0412 0.0325 1.0000
8.250 1.0949 0.01334 0.00727 -0.0408 0.0313 1.0000
8.500 1.1198 0.01372 0.00765 -0.0403 0.0302 1.0000
8.750 1.1439 0.01419 0.00812 -0.0397 0.0291 1.0000
9.000 1.1675 0.01471 0.00867 -0.0390 0.0283 1.0000
9.250 1.1919 0.01510 0.00910 -0.0385 0.0276 1.0000
9.500 1.2158 0.01553 0.00956 -0.0379 0.0270 1.0000
9.750 1.2393 0.01600 0.01006 -0.0372 0.0264 1.0000
10.000 1.2622 0.01652 0.01061 -0.0365 0.0259 1.0000
10.250 1.2837 0.01717 0.01129 -0.0356 0.0254 1.0000
10.500 1.3030 0.01805 0.01222 -0.0345 0.0248 1.0000
10.750 1.3252 0.01857 0.01280 -0.0337 0.0246 1.0000
11.000 1.3468 0.01914 0.01343 -0.0328 0.0243 1.0000
11.250 1.3676 0.01975 0.01411 -0.0318 0.0240 1.0000
11.500 1.3877 0.02040 0.01483 -0.0308 0.0237 1.0000
11.750 1.4071 0.02108 0.01557 -0.0297 0.0235 1.0000
12.000 1.4257 0.02180 0.01635 -0.0285 0.0232 1.0000
12.250 1.4433 0.02255 0.01717 -0.0272 0.0229 1.0000
12.500 1.4600 0.02332 0.01799 -0.0258 0.0227 1.0000
12.750 1.4751 0.02416 0.01890 -0.0242 0.0225 1.0000
13.000 1.4870 0.02509 0.01988 -0.0221 0.0222 1.0000
13.250 1.4947 0.02610 0.02096 -0.0195 0.0220 1.0000
13.500 1.4988 0.02735 0.02230 -0.0165 0.0218 1.0000
13.750 1.4996 0.02893 0.02398 -0.0136 0.0216 1.0000
14.000 1.4987 0.03075 0.02592 -0.0108 0.0215 1.0000
14.250 1.5047 0.03200 0.02728 -0.0089 0.0214 1.0000
14.500 1.5084 0.03353 0.02891 -0.0071 0.0213 1.0000
14.750 1.5114 0.03519 0.03069 -0.0055 0.0213 1.0000
15.000 1.5128 0.03708 0.03270 -0.0041 0.0212 1.0000
15.250 1.5124 0.03927 0.03500 -0.0030 0.0211 1.0000
15.500 1.5106 0.04172 0.03758 -0.0023 0.0210 1.0000
15.750 1.5070 0.04455 0.04054 -0.0019 0.0209 1.0000
16.000 1.5016 0.04777 0.04389 -0.0020 0.0209 1.0000
16.250 1.4943 0.05147 0.04773 -0.0027 0.0208 1.0000
16.500 1.4845 0.05580 0.05220 -0.0041 0.0207 1.0000
16.750 1.4718 0.06091 0.05747 -0.0063 0.0207 1.0000
17.000 1.4572 0.06680 0.06350 -0.0094 0.0206 1.0000
17.250 1.4384 0.07394 0.07081 -0.0136 0.0206 1.0000
17.500 1.4166 0.08221 0.07925 -0.0189 0.0206 1.0000
17.750 1.3898 0.09208 0.08930 -0.0254 0.0205 1.0000
18.000 1.3549 0.10402 0.10143 -0.0333 0.0206 1.0000
18.250 1.3127 0.11815 0.11576 -0.0427 0.0207 1.0000
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