GOE 195 AIRFOIL (goe195-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 195 AIRFOIL (goe195-il) Reynolds number: 100,000 Max Cl/Cd: 64.41 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe195-il-100000-n5.txt Download as CSV file: xf-goe195-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 195 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3278 0.09476 0.08994 -0.0283 1.0000 0.0728
-7.250 -0.3389 0.09341 0.08869 -0.0263 1.0000 0.0746
-7.000 -0.3560 0.09241 0.08783 -0.0290 1.0000 0.0774
-6.750 -0.3557 0.08957 0.08504 -0.0360 0.9990 0.0781
-6.500 -0.3349 0.08396 0.07943 -0.0400 0.9946 0.0789
-6.000 -0.2711 0.06596 0.06117 -0.0622 0.9820 0.0541
-5.750 -0.2480 0.06344 0.05861 -0.0630 0.9768 0.0526
-5.500 -0.2161 0.05845 0.05354 -0.0700 0.9708 0.0509
-5.250 -0.1726 0.05070 0.04558 -0.0826 0.9645 0.0491
-5.000 -0.1144 0.03885 0.03309 -0.1010 0.9596 0.0495
-4.750 -0.0677 0.03207 0.02548 -0.1105 0.9538 0.0485
-4.500 -0.0233 0.02824 0.02095 -0.1161 0.9497 0.0484
-4.250 0.0141 0.02589 0.01810 -0.1191 0.9437 0.0487
-4.000 0.0507 0.02429 0.01612 -0.1214 0.9379 0.0504
-3.750 0.0901 0.02286 0.01431 -0.1239 0.9340 0.0518
-3.500 0.1223 0.02172 0.01292 -0.1249 0.9263 0.0522
-3.250 0.1579 0.02067 0.01168 -0.1263 0.9204 0.0527
-3.000 0.1916 0.01982 0.01068 -0.1274 0.9137 0.0532
-2.750 0.2239 0.01910 0.00989 -0.1281 0.9059 0.0539
-2.500 0.2575 0.01832 0.00908 -0.1292 0.8990 0.0552
-2.250 0.2891 0.01776 0.00850 -0.1298 0.8899 0.0577
-2.000 0.3206 0.01731 0.00800 -0.1303 0.8805 0.0614
-1.750 0.3542 0.01685 0.00744 -0.1312 0.8722 0.0644
-1.500 0.3841 0.01645 0.00700 -0.1313 0.8609 0.0679
-1.250 0.4152 0.01605 0.00658 -0.1317 0.8503 0.0750
-1.000 0.4476 0.01548 0.00617 -0.1323 0.8400 0.1091
-0.750 0.4777 0.01512 0.00621 -0.1326 0.8277 0.2397
-0.500 0.5070 0.01508 0.00618 -0.1325 0.8146 0.2897
-0.250 0.5366 0.01499 0.00603 -0.1324 0.8014 0.3171
0.000 0.5662 0.01485 0.00589 -0.1324 0.7879 0.3401
0.250 0.5956 0.01471 0.00578 -0.1323 0.7742 0.3689
0.500 0.6245 0.01458 0.00573 -0.1322 0.7604 0.4071
0.750 0.6532 0.01448 0.00568 -0.1320 0.7465 0.4412
1.000 0.6814 0.01440 0.00566 -0.1316 0.7324 0.4837
1.250 0.7084 0.01428 0.00569 -0.1312 0.7182 0.5565
1.500 0.7300 0.01368 0.00566 -0.1293 0.7041 0.7554
2.000 0.7865 0.01393 0.00573 -0.1289 0.6748 1.0000
2.250 0.8134 0.01413 0.00582 -0.1285 0.6600 1.0000
2.500 0.8399 0.01434 0.00593 -0.1279 0.6441 1.0000
2.750 0.8661 0.01454 0.00603 -0.1274 0.6282 1.0000
3.000 0.8924 0.01476 0.00617 -0.1268 0.6136 1.0000
3.250 0.9188 0.01499 0.00635 -0.1264 0.6007 1.0000
3.500 0.9452 0.01524 0.00654 -0.1259 0.5893 1.0000
3.750 0.9716 0.01551 0.00675 -0.1254 0.5787 1.0000
4.000 0.9977 0.01580 0.00705 -0.1249 0.5676 1.0000
4.250 1.0235 0.01610 0.00732 -0.1244 0.5557 1.0000
4.500 1.0489 0.01643 0.00761 -0.1237 0.5424 1.0000
4.750 1.0738 0.01679 0.00794 -0.1230 0.5277 1.0000
5.000 1.0983 0.01715 0.00828 -0.1222 0.5121 1.0000
5.250 1.1224 0.01751 0.00865 -0.1213 0.4962 1.0000
5.500 1.1463 0.01787 0.00905 -0.1205 0.4801 1.0000
5.750 1.1699 0.01820 0.00947 -0.1196 0.4630 1.0000
6.000 1.1929 0.01853 0.00988 -0.1186 0.4437 1.0000
6.250 1.2148 0.01886 0.01024 -0.1174 0.4194 1.0000
6.500 1.2357 0.01924 0.01062 -0.1161 0.3880 1.0000
6.750 1.2555 0.01974 0.01105 -0.1147 0.3541 1.0000
7.000 1.2746 0.02036 0.01158 -0.1132 0.3225 1.0000
7.250 1.2928 0.02111 0.01222 -0.1116 0.2921 1.0000
7.500 1.3093 0.02201 0.01299 -0.1099 0.2596 1.0000
7.750 1.3249 0.02300 0.01387 -0.1081 0.2280 1.0000
8.000 1.3406 0.02397 0.01479 -0.1063 0.2000 1.0000
8.250 1.3547 0.02504 0.01577 -0.1044 0.1689 1.0000
8.500 1.3666 0.02628 0.01686 -0.1023 0.1393 1.0000
8.750 1.3771 0.02761 0.01808 -0.1000 0.1160 1.0000
9.000 1.3858 0.02904 0.01946 -0.0975 0.0970 1.0000
9.250 1.3941 0.03039 0.02082 -0.0948 0.0795 1.0000
9.500 1.4007 0.03178 0.02221 -0.0920 0.0663 1.0000
9.750 1.4061 0.03329 0.02372 -0.0892 0.0582 1.0000
10.000 1.4112 0.03485 0.02533 -0.0865 0.0525 1.0000
10.250 1.4137 0.03664 0.02714 -0.0838 0.0488 1.0000
10.500 1.4167 0.03847 0.02913 -0.0814 0.0459 1.0000
10.750 1.4179 0.04052 0.03129 -0.0791 0.0435 1.0000
11.000 1.4159 0.04294 0.03378 -0.0768 0.0415 1.0000
11.250 1.4153 0.04538 0.03635 -0.0749 0.0397 1.0000
11.500 1.4162 0.04778 0.03892 -0.0732 0.0380 1.0000
11.750 1.4163 0.05037 0.04166 -0.0717 0.0365 1.0000
12.000 1.4159 0.05309 0.04450 -0.0703 0.0353 1.0000
12.250 1.4148 0.05597 0.04747 -0.0692 0.0340 1.0000
12.500 1.4129 0.05902 0.05056 -0.0679 0.0328 1.0000
12.750 1.4142 0.06185 0.05356 -0.0668 0.0317 1.0000
13.000 1.4156 0.06474 0.05667 -0.0660 0.0305 1.0000
13.250 1.4162 0.06777 0.05990 -0.0653 0.0295 1.0000
13.500 1.4165 0.07092 0.06323 -0.0646 0.0287 1.0000
13.750 1.4159 0.07422 0.06670 -0.0641 0.0279 1.0000
14.000 1.4139 0.07772 0.07035 -0.0638 0.0272 1.0000
14.250 1.4111 0.08133 0.07410 -0.0638 0.0264 1.0000
14.500 1.4086 0.08499 0.07785 -0.0638 0.0257 1.0000
14.750 1.4057 0.08891 0.08185 -0.0636 0.0250 1.0000
15.000 1.3949 0.09401 0.08724 -0.0651 0.0247 1.0000
15.250 1.3830 0.09954 0.09306 -0.0671 0.0243 1.0000
15.500 1.3706 0.10544 0.09925 -0.0694 0.0241 1.0000
15.750 1.3570 0.11178 0.10585 -0.0723 0.0238 1.0000
16.000 1.3421 0.11864 0.11295 -0.0758 0.0237 1.0000
16.250 1.3261 0.12612 0.12065 -0.0800 0.0236 1.0000
16.500 1.3086 0.13439 0.12915 -0.0850 0.0236 1.0000
16.750 1.2895 0.14366 0.13864 -0.0911 0.0237 1.0000
17.000 1.2683 0.15426 0.14944 -0.0984 0.0238 1.0000
17.250 1.2444 0.16670 0.16206 -0.1070 0.0241 1.0000
17.500 1.2175 0.18166 0.17713 -0.1172 0.0245 1.0000
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