RAE(NPL) 5213 AIRFOIL (rae5213-il) Xfoil prediction polar at RE=50,000 Ncrit=5
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Airfoil: RAE(NPL) 5213 AIRFOIL (rae5213-il) Reynolds number: 50,000 Max Cl/Cd: 29.21 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-rae5213-il-50000-n5.txt Download as CSV file: xf-rae5213-il-50000-n5.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 = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.5253 0.11125 0.10339 -0.0204 1.0000 0.0624
-10.250 -0.5175 0.10762 0.09975 -0.0207 1.0000 0.0606
-10.000 -0.5148 0.10344 0.09562 -0.0221 1.0000 0.0591
-9.500 -0.5395 0.08838 0.08067 -0.0334 1.0000 0.0539
-9.250 -0.5405 0.08399 0.07632 -0.0353 1.0000 0.0533
-9.000 -0.5484 0.07902 0.07139 -0.0381 1.0000 0.0528
-8.750 -0.5610 0.07437 0.06676 -0.0406 1.0000 0.0522
-8.500 -0.5734 0.06987 0.06222 -0.0427 1.0000 0.0516
-8.250 -0.5829 0.06543 0.05765 -0.0441 1.0000 0.0511
-8.000 -0.5884 0.06121 0.05325 -0.0449 1.0000 0.0507
-7.750 -0.5900 0.05720 0.04900 -0.0452 1.0000 0.0509
-7.500 -0.5876 0.05348 0.04498 -0.0451 1.0000 0.0515
-7.250 -0.5818 0.04994 0.04106 -0.0448 1.0000 0.0522
-7.000 -0.5731 0.04650 0.03716 -0.0442 1.0000 0.0531
-6.750 -0.5610 0.04327 0.03340 -0.0434 1.0000 0.0538
-6.500 -0.5452 0.04056 0.03041 -0.0426 1.0000 0.0544
-6.250 -0.5275 0.03828 0.02798 -0.0417 1.0000 0.0555
-6.000 -0.5091 0.03632 0.02583 -0.0407 1.0000 0.0576
-5.750 -0.4896 0.03434 0.02351 -0.0397 1.0000 0.0601
-5.500 -0.4687 0.03244 0.02117 -0.0385 1.0000 0.0620
-5.250 -0.4483 0.03079 0.01954 -0.0373 1.0000 0.0641
-5.000 -0.4276 0.02947 0.01815 -0.0360 1.0000 0.0675
-4.750 -0.4061 0.02823 0.01668 -0.0345 1.0000 0.0710
-4.500 -0.3862 0.02702 0.01555 -0.0328 1.0000 0.0738
-4.250 -0.3666 0.02607 0.01457 -0.0312 1.0000 0.0783
-4.000 -0.3474 0.02515 0.01361 -0.0296 1.0000 0.0837
-3.750 -0.3285 0.02428 0.01274 -0.0281 1.0000 0.0897
-3.500 -0.3094 0.02340 0.01188 -0.0269 1.0000 0.0982
-3.250 -0.2891 0.02250 0.01102 -0.0260 1.0000 0.1113
-3.000 -0.2681 0.02147 0.01012 -0.0255 1.0000 0.1374
-2.750 -0.2475 0.01897 0.00924 -0.0263 1.0000 0.3594
-2.500 -0.2383 0.01902 0.01018 -0.0214 1.0000 0.5973
-2.250 -0.2267 0.01947 0.01067 -0.0172 1.0000 0.6722
-2.000 -0.2207 0.01984 0.01117 -0.0114 1.0000 0.7293
-1.750 -0.2176 0.02002 0.01145 -0.0049 1.0000 0.7792
-1.500 -0.2097 0.01997 0.01140 -0.0001 1.0000 0.8126
-1.250 -0.1828 0.01993 0.01122 -0.0001 0.9951 0.8282
-1.000 -0.1470 0.01996 0.01108 -0.0021 0.9867 0.8395
-0.750 -0.1111 0.02000 0.01098 -0.0042 0.9780 0.8511
-0.500 -0.0751 0.02005 0.01091 -0.0063 0.9692 0.8629
-0.250 -0.0375 0.02011 0.01089 -0.0085 0.9606 0.8744
0.000 -0.0003 0.02016 0.01090 -0.0108 0.9512 0.8865
0.250 0.0368 0.02021 0.01092 -0.0130 0.9414 0.8997
0.500 0.0811 0.02032 0.01102 -0.0166 0.9333 0.9126
0.750 0.1219 0.02039 0.01111 -0.0195 0.9228 0.9274
1.000 0.1686 0.02050 0.01126 -0.0236 0.9134 0.9437
1.250 0.2190 0.02059 0.01141 -0.0284 0.9037 0.9634
1.500 0.2622 0.02066 0.01154 -0.0320 0.8914 1.0000
1.750 0.3022 0.02075 0.01169 -0.0347 0.8792 1.0000
2.000 0.3439 0.02063 0.01164 -0.0370 0.8610 1.0000
2.250 0.3925 0.01976 0.01081 -0.0382 0.8228 1.0000
2.500 0.4330 0.01885 0.00986 -0.0376 0.7754 1.0000
2.750 0.4618 0.01861 0.00960 -0.0367 0.7386 1.0000
3.000 0.4888 0.01852 0.00949 -0.0357 0.6989 1.0000
3.250 0.5152 0.01846 0.00939 -0.0345 0.6482 1.0000
3.500 0.5394 0.01854 0.00924 -0.0327 0.5655 1.0000
3.750 0.5597 0.01916 0.00905 -0.0303 0.4208 1.0000
4.000 0.5748 0.02065 0.00956 -0.0285 0.2905 1.0000
4.250 0.5941 0.02199 0.01038 -0.0277 0.2348 1.0000
4.500 0.6161 0.02312 0.01126 -0.0272 0.2061 1.0000
4.750 0.6396 0.02415 0.01213 -0.0267 0.1875 1.0000
5.000 0.6639 0.02515 0.01303 -0.0264 0.1730 1.0000
5.250 0.6892 0.02621 0.01398 -0.0261 0.1616 1.0000
5.500 0.7160 0.02720 0.01502 -0.0260 0.1508 1.0000
5.750 0.7432 0.02833 0.01613 -0.0259 0.1419 1.0000
6.000 0.7704 0.02949 0.01730 -0.0258 0.1335 1.0000
6.250 0.7978 0.03080 0.01866 -0.0257 0.1259 1.0000
6.500 0.8240 0.03210 0.01999 -0.0255 0.1189 1.0000
6.750 0.8497 0.03362 0.02163 -0.0253 0.1125 1.0000
7.000 0.8742 0.03511 0.02326 -0.0250 0.1064 1.0000
7.250 0.8980 0.03680 0.02498 -0.0247 0.1014 1.0000
7.500 0.9198 0.03869 0.02723 -0.0241 0.0962 1.0000
7.750 0.9416 0.04040 0.02901 -0.0237 0.0920 1.0000
8.000 0.9610 0.04271 0.03159 -0.0230 0.0887 1.0000
8.250 0.9766 0.04528 0.03462 -0.0219 0.0851 1.0000
8.500 0.9933 0.04748 0.03704 -0.0211 0.0820 1.0000
8.750 1.0104 0.04970 0.03935 -0.0205 0.0799 1.0000
9.000 1.0182 0.05306 0.04314 -0.0192 0.0782 1.0000
9.250 1.0185 0.05690 0.04752 -0.0176 0.0764 1.0000
9.500 1.0162 0.06070 0.05172 -0.0162 0.0749 1.0000
9.750 1.0113 0.06445 0.05579 -0.0150 0.0736 1.0000
10.000 1.0018 0.06841 0.06001 -0.0138 0.0728 1.0000
10.250 0.9841 0.07260 0.06442 -0.0126 0.0724 1.0000
10.500 0.9553 0.07797 0.07000 -0.0128 0.0726 1.0000
10.750 0.9155 0.08590 0.07811 -0.0165 0.0732 1.0000
11.000 0.8695 0.09792 0.09023 -0.0251 0.0744 1.0000
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Polar data table (+)
Polar graphs
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