GOE 458 AIRFOIL (goe458-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 458 AIRFOIL (goe458-il) Reynolds number: 100,000 Max Cl/Cd: 64.62 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe458-il-100000-n5.txt Download as CSV file: xf-goe458-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 458 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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3081 0.10186 0.09750 -0.0309 1.0000 0.0357
-7.500 -0.3152 0.10044 0.09616 -0.0288 1.0000 0.0361
-7.250 -0.3230 0.09903 0.09482 -0.0267 0.9997 0.0368
-7.000 -0.3071 0.09535 0.09116 -0.0316 0.9932 0.0389
-6.750 -0.2873 0.09196 0.08779 -0.0416 0.9830 0.0415
-6.500 -0.2574 0.08808 0.08387 -0.0551 0.9731 0.0424
-6.250 -0.2417 0.08243 0.07825 -0.0572 0.9688 0.0432
-6.000 -0.2272 0.07846 0.07427 -0.0576 0.9627 0.0444
-5.750 -0.2042 0.07431 0.07006 -0.0617 0.9572 0.0458
-5.500 -0.1828 0.07060 0.06632 -0.0660 0.9497 0.0484
-5.250 -0.1272 0.06496 0.06045 -0.0853 0.9425 0.0550
-5.000 -0.1157 0.06055 0.05609 -0.0851 0.9352 0.0566
-4.750 -0.0830 0.05409 0.04947 -0.0899 0.9305 0.0307
-4.250 -0.0039 0.04113 0.03596 -0.1048 0.9184 0.0224
-4.000 0.0366 0.03563 0.03006 -0.1108 0.9150 0.0213
-3.750 0.0664 0.03129 0.02522 -0.1133 0.9068 0.0207
-3.500 0.1049 0.02710 0.02030 -0.1165 0.9027 0.0202
-3.250 0.1363 0.02435 0.01690 -0.1174 0.8962 0.0202
-3.000 0.1698 0.02216 0.01411 -0.1183 0.8907 0.0208
-2.750 0.2062 0.02072 0.01217 -0.1194 0.8867 0.0233
-2.500 0.2324 0.01923 0.01051 -0.1191 0.8784 0.0254
-2.250 0.2671 0.01812 0.00918 -0.1201 0.8739 0.0285
-2.000 0.2940 0.01740 0.00827 -0.1197 0.8652 0.0365
-1.750 0.3282 0.01621 0.00721 -0.1206 0.8603 0.0771
-1.500 0.3549 0.01606 0.00731 -0.1205 0.8512 0.2124
-1.250 0.3863 0.01590 0.00703 -0.1211 0.8448 0.2497
-1.000 0.4137 0.01569 0.00668 -0.1208 0.8361 0.2643
-0.750 0.4431 0.01548 0.00637 -0.1209 0.8282 0.2839
-0.500 0.4734 0.01524 0.00608 -0.1213 0.8206 0.3110
-0.250 0.5009 0.01502 0.00589 -0.1212 0.8115 0.3543
0.000 0.5302 0.01429 0.00571 -0.1215 0.8049 0.5277
0.500 0.5936 0.01358 0.00542 -0.1225 0.7875 1.0000
0.750 0.6212 0.01366 0.00536 -0.1223 0.7785 1.0000
1.000 0.6476 0.01378 0.00537 -0.1220 0.7692 1.0000
1.250 0.6769 0.01383 0.00532 -0.1221 0.7618 1.0000
1.500 0.7022 0.01399 0.00542 -0.1217 0.7517 1.0000
1.750 0.7291 0.01412 0.00550 -0.1214 0.7432 1.0000
2.000 0.7567 0.01424 0.00559 -0.1213 0.7350 1.0000
2.250 0.7823 0.01439 0.00574 -0.1208 0.7248 1.0000
2.500 0.8087 0.01450 0.00582 -0.1204 0.7140 1.0000
2.750 0.8349 0.01457 0.00588 -0.1198 0.7015 1.0000
3.000 0.8606 0.01466 0.00599 -0.1192 0.6875 1.0000
3.250 0.8858 0.01477 0.00610 -0.1184 0.6725 1.0000
3.500 0.9108 0.01490 0.00625 -0.1176 0.6571 1.0000
3.750 0.9359 0.01506 0.00650 -0.1169 0.6431 1.0000
4.000 0.9616 0.01526 0.00678 -0.1164 0.6319 1.0000
4.250 0.9869 0.01549 0.00712 -0.1158 0.6204 1.0000
4.500 1.0108 0.01571 0.00745 -0.1148 0.6039 1.0000
4.750 1.0275 0.01590 0.00753 -0.1121 0.5545 1.0000
5.000 1.0396 0.01636 0.00771 -0.1087 0.4705 1.0000
5.250 1.0396 0.01804 0.00825 -0.1038 0.2943 1.0000
5.500 1.0416 0.02025 0.00954 -0.1001 0.1630 1.0000
5.750 1.0404 0.02282 0.01121 -0.0959 0.0282 1.0000
6.000 1.0558 0.02389 0.01245 -0.0937 0.0221 1.0000
6.250 1.0695 0.02517 0.01397 -0.0913 0.0199 1.0000
6.500 1.0841 0.02630 0.01533 -0.0891 0.0187 1.0000
6.750 1.0970 0.02749 0.01681 -0.0867 0.0169 1.0000
7.000 1.1060 0.02883 0.01835 -0.0838 0.0154 1.0000
7.250 1.1121 0.03031 0.02000 -0.0806 0.0148 1.0000
7.500 1.1173 0.03191 0.02174 -0.0774 0.0145 1.0000
7.750 1.1235 0.03366 0.02359 -0.0744 0.0142 1.0000
8.000 1.1341 0.03555 0.02554 -0.0721 0.0139 1.0000
8.250 1.1545 0.03769 0.02770 -0.0709 0.0136 1.0000
8.750 1.2331 0.04548 0.03572 -0.0742 0.0115 1.0000
9.000 1.2589 0.04923 0.03975 -0.0740 0.0116 1.0000
9.250 1.2810 0.05341 0.04434 -0.0734 0.0119 1.0000
9.500 1.2904 0.05548 0.04674 -0.0709 0.0121 1.0000
9.750 1.2964 0.05736 0.04896 -0.0680 0.0124 1.0000
10.000 1.2980 0.05928 0.05128 -0.0645 0.0129 1.0000
10.250 1.2895 0.06138 0.05382 -0.0599 0.0135 1.0000
10.500 1.2798 0.06422 0.05708 -0.0560 0.0142 1.0000
10.750 1.2698 0.06750 0.06071 -0.0528 0.0148 1.0000
11.000 1.2581 0.07109 0.06460 -0.0503 0.0154 1.0000
11.250 1.2446 0.07496 0.06874 -0.0485 0.0159 1.0000
11.500 1.2294 0.07906 0.07309 -0.0473 0.0162 1.0000
11.750 1.2132 0.08350 0.07777 -0.0468 0.0165 1.0000
12.000 1.1960 0.08833 0.08283 -0.0471 0.0168 1.0000
12.250 1.1782 0.09356 0.08826 -0.0482 0.0170 1.0000
12.500 1.1604 0.09912 0.09402 -0.0502 0.0171 1.0000
12.750 1.1421 0.10522 0.10030 -0.0529 0.0171 1.0000
13.000 1.1239 0.11180 0.10705 -0.0565 0.0171 1.0000
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Polar data table (+)
Polar graphs
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