GOE 360 AIRFOIL (goe360-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 360 AIRFOIL (goe360-il) Reynolds number: 500,000 Max Cl/Cd: 104.62 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe360-il-500000-n5.txt Download as CSV file: xf-goe360-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 360 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.2779 0.11452 0.11222 -0.0256 0.9244 0.0105
-10.000 -0.2725 0.11139 0.10904 -0.0266 0.9124 0.0106
-9.500 -0.2613 0.10497 0.10256 -0.0290 0.8936 0.0110
-9.000 -0.2489 0.09874 0.09627 -0.0318 0.8770 0.0120
-8.750 -0.2404 0.09634 0.09385 -0.0330 0.8687 0.0124
-8.500 -0.2329 0.09355 0.09103 -0.0343 0.8591 0.0128
-8.250 -0.2261 0.09044 0.08790 -0.0360 0.8486 0.0130
-8.000 -0.2192 0.08732 0.08474 -0.0378 0.8377 0.0132
-7.750 -0.2122 0.08412 0.08151 -0.0399 0.8258 0.0134
-7.500 -0.2052 0.08084 0.07819 -0.0425 0.8133 0.0137
-7.250 -0.1934 0.07653 0.07384 -0.0476 0.8004 0.0147
-7.000 -0.1782 0.07436 0.07162 -0.0499 0.7850 0.0151
-6.750 -0.1620 0.07151 0.06868 -0.0533 0.7677 0.0158
-6.500 -0.1443 0.06792 0.06499 -0.0577 0.7487 0.0162
-6.250 -0.1247 0.06417 0.06112 -0.0624 0.7275 0.0165
-6.000 -0.1028 0.06018 0.05697 -0.0674 0.7068 0.0170
-5.750 -0.0457 0.04168 0.03838 -0.0696 0.6560 0.0213
-5.500 -0.0260 0.03753 0.03411 -0.0735 0.6466 0.0214
-5.250 -0.0092 0.03428 0.03079 -0.0751 0.6380 0.0211
-5.000 0.0131 0.03050 0.02687 -0.0784 0.6307 0.0211
-4.750 0.0377 0.02655 0.02276 -0.0819 0.6241 0.0222
-4.500 0.0576 0.02500 0.02116 -0.0824 0.6164 0.0230
-4.250 0.0907 0.02296 0.01889 -0.0853 0.6103 0.0264
-4.000 0.1174 0.02023 0.01598 -0.0870 0.6039 0.0265
-3.500 0.1702 0.03232 0.02741 -0.0934 0.6016 0.0266
-3.250 0.1984 0.03019 0.02506 -0.0941 0.5953 0.0267
-3.000 0.2257 0.02793 0.02262 -0.0947 0.5889 0.0267
-2.750 0.2494 0.02539 0.01995 -0.0957 0.5819 0.0259
-2.500 0.2773 0.02352 0.01788 -0.0961 0.5751 0.0258
-2.250 0.3055 0.02184 0.01597 -0.0963 0.5678 0.0257
-2.000 0.3351 0.02056 0.01443 -0.0962 0.5613 0.0265
-1.750 0.3627 0.01893 0.01259 -0.0964 0.5535 0.0262
-1.500 0.3908 0.01761 0.01104 -0.0965 0.5455 0.0262
-1.250 0.4191 0.01652 0.00972 -0.0965 0.5362 0.0264
-1.000 0.4473 0.01573 0.00872 -0.0964 0.5271 0.0266
-0.500 0.5030 0.01402 0.00662 -0.0964 0.5072 0.0272
-0.250 0.5303 0.01341 0.00590 -0.0965 0.4958 0.0279
0.000 0.5578 0.01305 0.00542 -0.0964 0.4835 0.0283
0.250 0.5851 0.01260 0.00483 -0.0963 0.4715 0.0282
0.500 0.6126 0.01224 0.00438 -0.0962 0.4602 0.0283
0.750 0.6398 0.01197 0.00403 -0.0962 0.4499 0.0286
1.000 0.6669 0.01178 0.00377 -0.0961 0.4396 0.0290
1.250 0.6941 0.01163 0.00356 -0.0960 0.4291 0.0296
1.500 0.7212 0.01151 0.00340 -0.0959 0.4197 0.0302
1.750 0.7482 0.01145 0.00328 -0.0958 0.4109 0.0308
2.000 0.7755 0.01137 0.00318 -0.0958 0.4033 0.0314
2.500 0.8299 0.01139 0.00315 -0.0958 0.3889 0.0334
2.750 0.8568 0.01141 0.00313 -0.0957 0.3815 0.0338
3.000 0.8841 0.01141 0.00313 -0.0957 0.3751 0.0342
3.250 0.9112 0.01141 0.00311 -0.0957 0.3686 0.0357
3.500 0.9382 0.01149 0.00317 -0.0957 0.3633 0.0375
3.750 0.9653 0.01156 0.00325 -0.0956 0.3580 0.0397
4.000 0.9921 0.01168 0.00335 -0.0956 0.3526 0.0427
4.250 1.0189 0.01180 0.00348 -0.0955 0.3476 0.0541
4.750 1.0685 0.01053 0.00394 -0.0949 0.3378 1.0000
5.000 1.0947 0.01074 0.00412 -0.0948 0.3336 1.0000
5.250 1.1214 0.01090 0.00429 -0.0947 0.3298 1.0000
5.500 1.1478 0.01109 0.00448 -0.0946 0.3258 1.0000
5.750 1.1737 0.01131 0.00468 -0.0945 0.3216 1.0000
6.000 1.1996 0.01153 0.00491 -0.0943 0.3178 1.0000
6.250 1.2257 0.01172 0.00512 -0.0942 0.3126 1.0000
6.500 1.2508 0.01199 0.00536 -0.0940 0.3056 1.0000
6.750 1.2764 0.01220 0.00559 -0.0938 0.2989 1.0000
7.000 1.3010 0.01250 0.00586 -0.0935 0.2901 1.0000
7.250 1.3263 0.01273 0.00611 -0.0933 0.2823 1.0000
7.500 1.3502 0.01306 0.00641 -0.0929 0.2739 1.0000
7.750 1.3749 0.01332 0.00670 -0.0926 0.2644 1.0000
8.000 1.3980 0.01371 0.00704 -0.0922 0.2498 1.0000
8.250 1.4193 0.01422 0.00746 -0.0915 0.2300 1.0000
8.500 1.4385 0.01490 0.00800 -0.0905 0.2019 1.0000
8.750 1.4378 0.01719 0.00966 -0.0870 0.1077 1.0000
9.000 1.4319 0.01963 0.01164 -0.0827 0.0340 1.0000
9.250 1.4394 0.02073 0.01271 -0.0800 0.0204 1.0000
9.500 1.4515 0.02156 0.01358 -0.0781 0.0174 1.0000
9.750 1.4635 0.02244 0.01451 -0.0763 0.0155 1.0000
10.000 1.4760 0.02332 0.01546 -0.0747 0.0145 1.0000
10.250 1.4870 0.02434 0.01657 -0.0731 0.0136 1.0000
10.500 1.4961 0.02555 0.01785 -0.0715 0.0127 1.0000
10.750 1.5024 0.02705 0.01944 -0.0698 0.0119 1.0000
11.000 1.5108 0.02842 0.02090 -0.0685 0.0114 1.0000
11.250 1.5187 0.02991 0.02248 -0.0673 0.0109 1.0000
11.500 1.5247 0.03163 0.02429 -0.0661 0.0104 1.0000
11.750 1.5293 0.03356 0.02632 -0.0650 0.0100 1.0000
12.000 1.5324 0.03573 0.02859 -0.0641 0.0096 1.0000
12.250 1.5337 0.03819 0.03115 -0.0633 0.0093 1.0000
12.500 1.5326 0.04105 0.03411 -0.0627 0.0091 1.0000
12.750 1.5281 0.04442 0.03759 -0.0623 0.0088 1.0000
13.000 1.5200 0.04837 0.04167 -0.0622 0.0086 1.0000
13.250 1.5168 0.05179 0.04520 -0.0622 0.0085 1.0000
13.500 1.5124 0.05541 0.04894 -0.0622 0.0083 1.0000
13.750 1.5072 0.05924 0.05288 -0.0624 0.0081 1.0000
14.000 1.5008 0.06330 0.05707 -0.0628 0.0080 1.0000
14.250 1.4933 0.06757 0.06145 -0.0632 0.0078 1.0000
14.500 1.4855 0.07200 0.06600 -0.0638 0.0077 1.0000
14.750 1.4776 0.07653 0.07063 -0.0645 0.0075 1.0000
15.000 1.4694 0.08112 0.07534 -0.0653 0.0073 1.0000
15.250 1.4613 0.08581 0.08013 -0.0662 0.0072 1.0000
15.500 1.4536 0.09049 0.08491 -0.0671 0.0071 1.0000
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