GOE 513 AIRFOIL (goe513-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 513 AIRFOIL (goe513-il) Reynolds number: 1,000,000 Max Cl/Cd: 76.8 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe513-il-1000000-n5.txt Download as CSV file: xf-goe513-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 513 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.250 -0.6266 0.07762 0.07484 -0.1108 0.9831 0.0211
-17.000 -0.6483 0.07081 0.06793 -0.1158 0.9825 0.0212
-16.750 -0.6718 0.06389 0.06090 -0.1212 0.9819 0.0213
-16.500 -0.7113 0.05579 0.05266 -0.1266 0.9798 0.0212
-16.250 -0.7386 0.04876 0.04553 -0.1319 0.9773 0.0213
-16.000 -0.7566 0.03871 0.03525 -0.1433 0.9754 0.0214
-15.750 -0.7624 0.03428 0.03064 -0.1471 0.9735 0.0215
-15.500 -0.7603 0.03154 0.02777 -0.1486 0.9717 0.0216
-15.250 -0.7521 0.02955 0.02567 -0.1494 0.9702 0.0217
-15.000 -0.7401 0.02786 0.02387 -0.1501 0.9689 0.0218
-14.750 -0.7367 0.02669 0.02261 -0.1481 0.9655 0.0220
-14.500 -0.7278 0.02554 0.02138 -0.1468 0.9625 0.0221
-14.250 -0.7133 0.02451 0.02025 -0.1461 0.9598 0.0222
-14.000 -0.6940 0.02345 0.01910 -0.1463 0.9577 0.0224
-13.750 -0.6714 0.02241 0.01796 -0.1470 0.9562 0.0225
-13.500 -0.6434 0.02157 0.01703 -0.1483 0.9550 0.0227
-13.250 -0.6350 0.02092 0.01631 -0.1455 0.9509 0.0228
-13.000 -0.6195 0.02024 0.01556 -0.1440 0.9467 0.0229
-12.750 -0.5974 0.01959 0.01483 -0.1437 0.9439 0.0230
-12.500 -0.5706 0.01897 0.01413 -0.1442 0.9415 0.0231
-12.250 -0.5445 0.01839 0.01348 -0.1445 0.9394 0.0232
-12.000 -0.5403 0.01801 0.01305 -0.1401 0.9344 0.0233
-11.750 -0.5301 0.01732 0.01230 -0.1372 0.9295 0.0235
-11.500 -0.5080 0.01672 0.01164 -0.1366 0.9254 0.0237
-11.250 -0.4979 0.01628 0.01115 -0.1333 0.9198 0.0238
-11.000 -0.4856 0.01590 0.01074 -0.1303 0.9136 0.0240
-10.750 -0.4655 0.01542 0.01020 -0.1289 0.9087 0.0241
-10.500 -0.4550 0.01511 0.00986 -0.1254 0.9010 0.0242
-10.250 -0.4341 0.01479 0.00948 -0.1241 0.8924 0.0245
-10.000 -0.4181 0.01447 0.00910 -0.1217 0.8796 0.0246
-9.750 -0.3982 0.01413 0.00868 -0.1201 0.8646 0.0247
-9.500 -0.3781 0.01385 0.00829 -0.1184 0.8456 0.0250
-9.250 -0.3613 0.01365 0.00795 -0.1161 0.8191 0.0251
-9.000 -0.3487 0.01353 0.00766 -0.1128 0.7905 0.0253
-8.750 -0.3351 0.01337 0.00738 -0.1097 0.7702 0.0254
-8.250 -0.3015 0.01303 0.00687 -0.1050 0.7452 0.0259
-8.000 -0.2841 0.01287 0.00664 -0.1027 0.7353 0.0261
-7.750 -0.2650 0.01267 0.00638 -0.1008 0.7262 0.0263
-7.500 -0.2471 0.01253 0.00617 -0.0986 0.7165 0.0265
-7.250 -0.2269 0.01236 0.00594 -0.0969 0.7076 0.0267
-7.000 -0.2084 0.01221 0.00572 -0.0948 0.6984 0.0269
-6.750 -0.1878 0.01204 0.00551 -0.0931 0.6901 0.0270
-6.500 -0.1693 0.01186 0.00527 -0.0910 0.6798 0.0272
-6.250 -0.1508 0.01166 0.00501 -0.0889 0.6663 0.0275
-6.000 -0.1332 0.01151 0.00480 -0.0866 0.6504 0.0278
-5.750 -0.1188 0.01145 0.00463 -0.0836 0.6237 0.0281
-5.500 -0.1131 0.01158 0.00453 -0.0788 0.5687 0.0284
-5.250 -0.0998 0.01161 0.00443 -0.0756 0.5402 0.0286
-5.000 -0.0835 0.01157 0.00430 -0.0731 0.5250 0.0290
-4.750 -0.0670 0.01151 0.00418 -0.0705 0.5152 0.0292
-4.500 -0.0485 0.01142 0.00405 -0.0684 0.5076 0.0296
-4.250 -0.0304 0.01135 0.00394 -0.0661 0.5005 0.0300
-4.000 -0.0113 0.01127 0.00383 -0.0641 0.4947 0.0303
-3.750 0.0092 0.01118 0.00371 -0.0624 0.4894 0.0307
-3.500 0.0286 0.01112 0.00362 -0.0605 0.4823 0.0311
-3.250 0.0480 0.01106 0.00351 -0.0586 0.4761 0.0316
-3.000 0.0691 0.01096 0.00341 -0.0570 0.4703 0.0325
-2.750 0.0888 0.01091 0.00333 -0.0551 0.4635 0.0332
-2.500 0.1079 0.01089 0.00327 -0.0531 0.4558 0.0341
-2.250 0.1287 0.01084 0.00321 -0.0515 0.4494 0.0350
-2.000 0.1491 0.01082 0.00316 -0.0498 0.4438 0.0358
-1.750 0.1692 0.01079 0.00312 -0.0481 0.4393 0.0374
-1.500 0.1906 0.01075 0.00308 -0.0466 0.4358 0.0391
-1.250 0.2116 0.01071 0.00304 -0.0450 0.4314 0.0417
-1.000 0.2319 0.01068 0.00302 -0.0433 0.4264 0.0460
-0.750 0.2510 0.01066 0.00299 -0.0414 0.4206 0.0553
-0.500 0.2685 0.01036 0.00290 -0.0392 0.4169 0.1159
-0.250 0.2847 0.01014 0.00291 -0.0368 0.4107 0.1831
0.000 0.3040 0.01016 0.00295 -0.0350 0.4053 0.1977
0.250 0.3236 0.01019 0.00299 -0.0332 0.4004 0.2072
0.500 0.3446 0.01023 0.00303 -0.0317 0.3954 0.2150
0.750 0.3648 0.01028 0.00307 -0.0301 0.3893 0.2208
1.000 0.3846 0.01035 0.00312 -0.0284 0.3837 0.2258
1.250 0.4058 0.01040 0.00317 -0.0269 0.3783 0.2315
1.500 0.4257 0.01048 0.00322 -0.0253 0.3717 0.2359
1.750 0.4451 0.01056 0.00330 -0.0235 0.3656 0.2423
2.000 0.4652 0.01065 0.00336 -0.0219 0.3574 0.2457
2.250 0.4846 0.01077 0.00345 -0.0202 0.3499 0.2496
2.500 0.5052 0.01087 0.00352 -0.0188 0.3424 0.2537
2.750 0.5242 0.01100 0.00362 -0.0170 0.3345 0.2574
3.000 0.5440 0.01110 0.00372 -0.0155 0.3277 0.2622
3.250 0.5633 0.01124 0.00383 -0.0138 0.3198 0.2660
3.500 0.5829 0.01139 0.00394 -0.0122 0.3123 0.2693
3.750 0.6025 0.01154 0.00406 -0.0107 0.3041 0.2727
4.000 0.6218 0.01169 0.00420 -0.0091 0.2970 0.2791
4.250 0.6413 0.01184 0.00434 -0.0076 0.2894 0.2836
4.500 0.6597 0.01204 0.00450 -0.0059 0.2820 0.2885
4.750 0.6793 0.01220 0.00465 -0.0045 0.2755 0.2940
5.000 0.6979 0.01240 0.00483 -0.0028 0.2682 0.3004
5.250 0.7177 0.01258 0.00500 -0.0015 0.2624 0.3063
5.500 0.7368 0.01277 0.00519 0.0000 0.2554 0.3141
5.750 0.7550 0.01300 0.00541 0.0016 0.2495 0.3225
6.000 0.7749 0.01317 0.00560 0.0028 0.2455 0.3332
6.250 0.7948 0.01334 0.00581 0.0041 0.2415 0.3486
6.500 0.8141 0.01353 0.00605 0.0053 0.2371 0.3765
7.000 1.0267 0.01345 0.00749 -0.0305 0.2241 0.9755
7.250 1.0425 0.01381 0.00783 -0.0284 0.2210 0.9807
7.500 1.0701 0.01418 0.00819 -0.0290 0.2174 0.9828
7.750 1.1012 0.01449 0.00850 -0.0303 0.2158 0.9843
8.000 1.1320 0.01479 0.00881 -0.0316 0.2142 0.9862
8.250 1.1626 0.01514 0.00916 -0.0328 0.2122 0.9884
8.500 1.1911 0.01551 0.00954 -0.0337 0.2102 0.9906
8.750 1.2132 0.01587 0.00990 -0.0332 0.2084 0.9920
9.000 1.2351 0.01628 0.01031 -0.0328 0.2062 0.9931
9.250 1.2699 0.01669 0.01071 -0.0352 0.2035 0.9947
9.500 1.2939 0.01710 0.01112 -0.0353 0.2010 0.9957
9.750 1.3209 0.01742 0.01147 -0.0360 0.2002 0.9968
10.000 1.3506 0.01777 0.01185 -0.0373 0.1992 0.9981
10.250 1.3768 0.01815 0.01225 -0.0379 0.1972 0.9990
10.500 1.4010 0.01857 0.01268 -0.0382 0.1945 0.9997
10.750 1.4207 0.01902 0.01315 -0.0376 0.1929 1.0000
11.000 1.4336 0.01951 0.01366 -0.0357 0.1915 1.0000
11.250 1.4442 0.02012 0.01427 -0.0335 0.1877 1.0000
11.500 1.4559 0.02071 0.01488 -0.0315 0.1861 1.0000
11.750 1.4703 0.02118 0.01539 -0.0299 0.1848 1.0000
12.000 1.4843 0.02169 0.01593 -0.0284 0.1834 1.0000
12.250 1.4973 0.02227 0.01655 -0.0267 0.1810 1.0000
12.500 1.5099 0.02290 0.01719 -0.0251 0.1791 1.0000
12.750 1.5211 0.02362 0.01794 -0.0234 0.1770 1.0000
13.000 1.5309 0.02445 0.01878 -0.0216 0.1740 1.0000
13.250 1.5410 0.02531 0.01966 -0.0199 0.1709 1.0000
13.500 1.5533 0.02604 0.02045 -0.0186 0.1704 1.0000
13.750 1.5649 0.02685 0.02129 -0.0172 0.1684 1.0000
14.000 1.5748 0.02778 0.02224 -0.0157 0.1647 1.0000
14.250 1.5820 0.02893 0.02340 -0.0141 0.1610 1.0000
14.500 1.5894 0.03010 0.02460 -0.0126 0.1583 1.0000
14.750 1.5994 0.03112 0.02566 -0.0113 0.1557 1.0000
15.000 1.6050 0.03249 0.02704 -0.0099 0.1505 1.0000
15.250 1.6094 0.03397 0.02855 -0.0084 0.1469 1.0000
15.500 1.6125 0.03561 0.03019 -0.0070 0.1406 1.0000
15.750 1.6096 0.03779 0.03236 -0.0053 0.1335 1.0000
16.000 1.6066 0.04006 0.03463 -0.0038 0.1256 1.0000
16.250 1.5989 0.04281 0.03738 -0.0022 0.1174 1.0000
16.500 1.5870 0.04606 0.04062 -0.0008 0.1087 1.0000
16.750 1.5731 0.04970 0.04426 0.0004 0.1003 1.0000
17.000 1.5570 0.05376 0.04834 0.0013 0.0915 1.0000
17.250 1.5354 0.05860 0.05319 0.0019 0.0819 1.0000
17.500 1.5061 0.06451 0.05911 0.0022 0.0706 1.0000
17.750 1.4803 0.07013 0.06476 0.0022 0.0620 1.0000
18.000 1.4539 0.07598 0.07065 0.0020 0.0545 1.0000
18.500 1.4101 0.08699 0.08177 0.0010 0.0444 1.0000
18.750 1.3706 0.09506 0.08988 -0.0002 0.0335 1.0000
19.000 1.3555 0.10004 0.09494 -0.0011 0.0307 1.0000
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