GOE 503 AIRFOIL (goe503-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 503 AIRFOIL (goe503-il) Reynolds number: 200,000 Max Cl/Cd: 68.47 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe503-il-200000.txt Download as CSV file: xf-goe503-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 503 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.0189 0.09087 0.08752 -0.1079 0.9430 0.0673
-9.500 0.0015 0.08838 0.08502 -0.1081 0.9344 0.0689
-9.250 -0.2258 0.03911 0.03509 -0.1384 0.9008 0.0396
-9.000 -0.2448 0.03309 0.02829 -0.1364 0.8881 0.0402
-8.750 -0.2291 0.02968 0.02437 -0.1367 0.8823 0.0421
-8.500 -0.2092 0.02909 0.02379 -0.1356 0.8725 0.0438
-8.250 -0.1844 0.02701 0.02128 -0.1361 0.8667 0.0469
-8.000 -0.1743 0.02512 0.01899 -0.1335 0.8563 0.0491
-7.750 -0.1409 0.02425 0.01809 -0.1349 0.8506 0.0530
-7.500 -0.1263 0.02305 0.01656 -0.1326 0.8404 0.0576
-7.250 -0.0929 0.02268 0.01615 -0.1338 0.8343 0.0642
-7.000 -0.0750 0.02200 0.01539 -0.1320 0.8245 0.0694
-6.750 -0.0436 0.02172 0.01481 -0.1326 0.8180 0.0764
-6.500 -0.0238 0.02132 0.01449 -0.1312 0.8081 0.0810
-6.250 0.0079 0.02106 0.01395 -0.1318 0.8015 0.0873
-6.000 0.0260 0.02048 0.01330 -0.1300 0.7918 0.0915
-5.750 0.0577 0.02046 0.01320 -0.1308 0.7852 0.0977
-5.500 0.0759 0.02012 0.01262 -0.1288 0.7756 0.1025
-5.250 0.1068 0.01959 0.01207 -0.1295 0.7689 0.1075
-5.000 0.1266 0.01921 0.01157 -0.1278 0.7596 0.1114
-4.750 0.1572 0.01873 0.01076 -0.1281 0.7531 0.1155
-4.500 0.1772 0.01812 0.01017 -0.1266 0.7442 0.1201
-4.250 0.2069 0.01779 0.00971 -0.1269 0.7374 0.1255
-4.000 0.2283 0.01754 0.00929 -0.1254 0.7288 0.1308
-3.750 0.2564 0.01713 0.00889 -0.1255 0.7219 0.1380
-3.500 0.2793 0.01700 0.00863 -0.1244 0.7143 0.1465
-3.250 0.3048 0.01681 0.00847 -0.1239 0.7070 0.1552
-3.000 0.3304 0.01667 0.00824 -0.1233 0.7002 0.1651
-2.750 0.3529 0.01667 0.00820 -0.1221 0.6926 0.1749
-2.500 0.3825 0.01658 0.00804 -0.1224 0.6869 0.1856
-2.250 0.4014 0.01656 0.00799 -0.1206 0.6790 0.1953
-2.000 0.4280 0.01648 0.00788 -0.1203 0.6728 0.2056
-1.750 0.4519 0.01641 0.00779 -0.1195 0.6665 0.2162
-1.500 0.4742 0.01643 0.00774 -0.1183 0.6596 0.2280
-1.250 0.5027 0.01634 0.00762 -0.1184 0.6544 0.2416
-1.000 0.5221 0.01630 0.00765 -0.1168 0.6476 0.2535
-0.750 0.5466 0.01622 0.00755 -0.1161 0.6416 0.2664
-0.500 0.5756 0.01619 0.00742 -0.1163 0.6368 0.2801
-0.250 0.5930 0.01614 0.00748 -0.1143 0.6299 0.2909
0.000 0.6183 0.01607 0.00740 -0.1138 0.6245 0.3036
0.250 0.6447 0.01604 0.00735 -0.1135 0.6196 0.3181
0.500 0.6630 0.01604 0.00742 -0.1116 0.6132 0.3320
0.750 0.6881 0.01598 0.00736 -0.1111 0.6081 0.3484
1.000 0.7129 0.01593 0.00734 -0.1106 0.6033 0.3677
1.250 0.7292 0.01588 0.00743 -0.1083 0.5973 0.3913
1.500 0.7493 0.01566 0.00737 -0.1068 0.5923 0.4357
1.750 0.9745 0.01535 0.00811 -0.1475 0.5824 0.9996
2.000 0.9965 0.01547 0.00815 -0.1465 0.5772 1.0000
2.250 1.0218 0.01561 0.00814 -0.1461 0.5728 1.0000
2.500 1.0335 0.01580 0.00838 -0.1432 0.5670 1.0000
2.750 1.0520 0.01595 0.00848 -0.1414 0.5616 1.0000
3.000 1.0767 0.01610 0.00851 -0.1410 0.5572 1.0000
3.250 1.0893 0.01634 0.00879 -0.1382 0.5519 1.0000
3.500 1.1058 0.01651 0.00895 -0.1361 0.5464 1.0000
3.750 1.1297 0.01668 0.00901 -0.1355 0.5418 1.0000
4.000 1.1441 0.01694 0.00929 -0.1331 0.5368 1.0000
4.250 1.1584 0.01716 0.00952 -0.1306 0.5314 1.0000
4.500 1.1809 0.01733 0.00962 -0.1297 0.5266 1.0000
4.750 1.1984 0.01760 0.00987 -0.1279 0.5218 1.0000
5.000 1.2096 0.01784 0.01017 -0.1248 0.5162 1.0000
5.250 1.2304 0.01803 0.01032 -0.1236 0.5114 1.0000
5.500 1.2523 0.01830 0.01053 -0.1227 0.5067 1.0000
5.750 1.2592 0.01857 0.01088 -0.1187 0.5010 1.0000
6.000 1.2778 0.01873 0.01101 -0.1171 0.4955 1.0000
6.250 1.2968 0.01896 0.01120 -0.1156 0.4900 1.0000
6.500 1.3011 0.01917 0.01147 -0.1111 0.4834 1.0000
6.750 1.3215 0.01930 0.01154 -0.1099 0.4777 1.0000
7.000 1.3311 0.01959 0.01187 -0.1065 0.4721 1.0000
7.250 1.3401 0.01986 0.01219 -0.1031 0.4666 1.0000
7.500 1.3610 0.02007 0.01235 -0.1020 0.4618 1.0000
7.750 1.3708 0.02038 0.01270 -0.0988 0.4568 1.0000
8.000 1.3735 0.02065 0.01304 -0.0942 0.4513 1.0000
8.250 1.3915 0.02086 0.01322 -0.0926 0.4462 1.0000
8.500 1.4029 0.02119 0.01359 -0.0899 0.4411 1.0000
8.750 1.4059 0.02155 0.01402 -0.0856 0.4352 1.0000
9.000 1.4241 0.02179 0.01425 -0.0842 0.4302 1.0000
9.250 1.4353 0.02221 0.01472 -0.0816 0.4251 1.0000
9.500 1.4400 0.02267 0.01527 -0.0780 0.4194 1.0000
9.750 1.4581 0.02291 0.01546 -0.0766 0.4138 1.0000
10.000 1.4602 0.02348 0.01614 -0.0728 0.4075 1.0000
10.250 1.4656 0.02392 0.01662 -0.0695 0.4006 1.0000
10.500 1.4737 0.02441 0.01711 -0.0668 0.3937 1.0000
10.750 1.4737 0.02511 0.01789 -0.0630 0.3863 1.0000
11.000 1.4837 0.02564 0.01840 -0.0608 0.3792 1.0000
11.250 1.4826 0.02660 0.01947 -0.0573 0.3719 1.0000
11.500 1.4950 0.02715 0.01996 -0.0556 0.3649 1.0000
11.750 1.4898 0.02843 0.02139 -0.0520 0.3570 1.0000
12.000 1.5012 0.02910 0.02200 -0.0504 0.3499 1.0000
12.250 1.4956 0.03064 0.02370 -0.0472 0.3419 1.0000
12.500 1.5011 0.03169 0.02470 -0.0452 0.3339 1.0000
12.750 1.4980 0.03337 0.02652 -0.0427 0.3259 1.0000
13.000 1.5031 0.03461 0.02774 -0.0410 0.3184 1.0000
13.250 1.4997 0.03654 0.02980 -0.0389 0.3101 1.0000
13.500 1.5022 0.03811 0.03136 -0.0372 0.3025 1.0000
13.750 1.4993 0.04022 0.03357 -0.0355 0.2941 1.0000
14.000 1.4958 0.04244 0.03584 -0.0339 0.2849 1.0000
14.250 1.4934 0.04467 0.03808 -0.0325 0.2763 1.0000
14.500 1.4882 0.04730 0.04081 -0.0312 0.2670 1.0000
14.750 1.4852 0.04975 0.04324 -0.0301 0.2588 1.0000
15.000 1.4780 0.05281 0.04642 -0.0291 0.2489 1.0000
15.250 1.4721 0.05580 0.04946 -0.0282 0.2399 1.0000
15.500 1.4635 0.05911 0.05275 -0.0274 0.2301 1.0000
15.750 1.4531 0.06284 0.05656 -0.0268 0.2189 1.0000
16.000 1.4402 0.06692 0.06065 -0.0264 0.2066 1.0000
16.250 1.4252 0.07137 0.06509 -0.0260 0.1933 1.0000
16.500 1.4096 0.07596 0.06968 -0.0259 0.1800 1.0000
16.750 1.3935 0.08075 0.07444 -0.0259 0.1665 1.0000
17.000 1.3764 0.08578 0.07946 -0.0260 0.1521 1.0000
17.250 1.3576 0.09111 0.08476 -0.0263 0.1355 1.0000
17.500 1.3351 0.09703 0.09059 -0.0270 0.1101 1.0000
17.750 1.3025 0.10446 0.09783 -0.0280 0.0777 1.0000
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