GOE 593 AIRFOIL (goe593-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 593 AIRFOIL (goe593-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.09 at α=2.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe593-il-1000000.txt Download as CSV file: xf-goe593-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 593 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.9737 0.03640 0.03373 -0.0914 1.0000 0.0126
-14.000 -1.0030 0.03428 0.03151 -0.0866 1.0000 0.0127
-13.750 -1.0256 0.03288 0.03002 -0.0805 1.0000 0.0127
-13.500 -1.0139 0.03130 0.02834 -0.0803 0.9989 0.0129
-13.250 -0.9885 0.02971 0.02664 -0.0823 0.9968 0.0132
-13.000 -0.9625 0.02814 0.02494 -0.0842 0.9948 0.0135
-12.750 -0.9357 0.02707 0.02375 -0.0855 0.9930 0.0139
-12.500 -0.9130 0.02557 0.02209 -0.0864 0.9900 0.0142
-12.250 -0.8860 0.02441 0.02077 -0.0876 0.9877 0.0145
-12.000 -0.8623 0.02248 0.01862 -0.0888 0.9856 0.0149
-11.750 -0.8337 0.02131 0.01736 -0.0903 0.9844 0.0154
-11.500 -0.8090 0.02067 0.01666 -0.0902 0.9810 0.0157
-11.250 -0.7809 0.02020 0.01615 -0.0907 0.9781 0.0161
-11.000 -0.7509 0.01965 0.01554 -0.0917 0.9761 0.0166
-10.750 -0.7207 0.01889 0.01468 -0.0927 0.9745 0.0171
-10.500 -0.6890 0.01828 0.01396 -0.0939 0.9734 0.0176
-10.250 -0.6580 0.01742 0.01296 -0.0952 0.9723 0.0180
-10.000 -0.6399 0.01651 0.01199 -0.0937 0.9660 0.0187
-9.750 -0.6094 0.01612 0.01158 -0.0945 0.9638 0.0192
-9.500 -0.5773 0.01579 0.01122 -0.0955 0.9622 0.0199
-9.250 -0.5445 0.01539 0.01076 -0.0967 0.9607 0.0206
-9.000 -0.5107 0.01496 0.01025 -0.0981 0.9594 0.0213
-8.750 -0.4879 0.01451 0.00971 -0.0972 0.9527 0.0217
-8.500 -0.4581 0.01354 0.00867 -0.0981 0.9494 0.0226
-8.250 -0.4221 0.01319 0.00832 -0.0999 0.9472 0.0234
-8.000 -0.3896 0.01292 0.00801 -0.1010 0.9432 0.0243
-7.750 -0.3590 0.01260 0.00762 -0.1016 0.9374 0.0251
-7.500 -0.3235 0.01231 0.00726 -0.1033 0.9332 0.0258
-7.250 -0.2961 0.01145 0.00633 -0.1035 0.9264 0.0269
-7.000 -0.2653 0.01112 0.00597 -0.1042 0.9200 0.0278
-6.750 -0.2351 0.01086 0.00567 -0.1047 0.9135 0.0288
-6.500 -0.2075 0.01061 0.00536 -0.1046 0.9056 0.0297
-6.250 -0.1789 0.01038 0.00506 -0.1047 0.8986 0.0304
-6.000 -0.1529 0.01022 0.00485 -0.1042 0.8905 0.0309
-5.750 -0.1292 0.00962 0.00418 -0.1034 0.8828 0.0325
-5.500 -0.1045 0.00939 0.00393 -0.1027 0.8742 0.0335
-5.250 -0.0783 0.00921 0.00370 -0.1022 0.8666 0.0346
-5.000 -0.0535 0.00901 0.00346 -0.1015 0.8576 0.0356
-4.750 -0.0277 0.00888 0.00327 -0.1009 0.8489 0.0365
-4.500 -0.0036 0.00861 0.00293 -0.1000 0.8386 0.0379
-4.250 0.0203 0.00839 0.00268 -0.0990 0.8266 0.0396
-4.000 0.0446 0.00826 0.00249 -0.0981 0.8130 0.0412
-3.750 0.0691 0.00815 0.00231 -0.0972 0.7991 0.0429
-3.500 0.0934 0.00802 0.00212 -0.0963 0.7864 0.0455
-3.250 0.1178 0.00789 0.00196 -0.0954 0.7744 0.0496
-3.000 0.1423 0.00775 0.00181 -0.0946 0.7624 0.0570
-2.750 0.1661 0.00756 0.00169 -0.0937 0.7505 0.0823
-2.500 0.1905 0.00746 0.00163 -0.0928 0.7394 0.1057
-2.250 0.2152 0.00742 0.00157 -0.0921 0.7274 0.1195
-2.000 0.2404 0.00738 0.00152 -0.0914 0.7157 0.1308
-1.750 0.2654 0.00734 0.00147 -0.0907 0.7047 0.1428
-1.500 0.2900 0.00730 0.00142 -0.0899 0.6942 0.1581
-1.250 0.3150 0.00720 0.00138 -0.0892 0.6838 0.1833
-1.000 0.3388 0.00705 0.00137 -0.0884 0.6741 0.2376
-0.750 0.3625 0.00690 0.00135 -0.0875 0.6646 0.2957
-0.500 0.3842 0.00657 0.00134 -0.0863 0.6558 0.4085
-0.250 0.4016 0.00612 0.00136 -0.0842 0.6464 0.5859
0.000 0.4188 0.00574 0.00140 -0.0818 0.6370 0.7260
0.250 0.4357 0.00547 0.00147 -0.0791 0.6274 0.8434
0.500 0.4654 0.00543 0.00156 -0.0793 0.6167 0.9125
0.750 0.5138 0.00554 0.00166 -0.0837 0.6052 0.9480
1.000 0.5595 0.00569 0.00175 -0.0876 0.5929 0.9628
1.250 0.5966 0.00584 0.00183 -0.0895 0.5799 0.9729
1.500 0.6315 0.00601 0.00192 -0.0910 0.5649 0.9805
1.750 0.6701 0.00618 0.00200 -0.0933 0.5459 0.9855
2.000 0.7091 0.00637 0.00209 -0.0958 0.5254 0.9900
2.250 0.7481 0.00660 0.00220 -0.0983 0.5022 0.9946
2.500 0.7953 0.00684 0.00230 -0.1027 0.4738 0.9988
2.750 0.8243 0.00704 0.00238 -0.1031 0.4498 1.0000
3.000 0.8420 0.00722 0.00246 -0.1010 0.4290 1.0000
3.500 0.8777 0.00761 0.00267 -0.0970 0.3917 1.0000
3.750 0.8962 0.00780 0.00279 -0.0950 0.3761 1.0000
4.000 0.9148 0.00799 0.00291 -0.0931 0.3620 1.0000
4.500 0.9524 0.00838 0.00318 -0.0895 0.3336 1.0000
4.750 0.9721 0.00856 0.00331 -0.0878 0.3231 1.0000
5.000 0.9911 0.00876 0.00347 -0.0860 0.3116 1.0000
5.250 1.0103 0.00896 0.00362 -0.0842 0.3012 1.0000
5.500 1.0305 0.00913 0.00377 -0.0827 0.2930 1.0000
5.750 1.0496 0.00934 0.00394 -0.0809 0.2844 1.0000
6.000 1.0703 0.00949 0.00409 -0.0795 0.2776 1.0000
6.500 1.1099 0.00988 0.00444 -0.0763 0.2620 1.0000
6.750 1.1284 0.01014 0.00465 -0.0745 0.2528 1.0000
7.000 1.1489 0.01031 0.00483 -0.0731 0.2458 1.0000
7.250 1.1661 0.01056 0.00504 -0.0711 0.2385 1.0000
7.500 1.1850 0.01072 0.00522 -0.0693 0.2335 1.0000
7.750 1.2024 0.01094 0.00544 -0.0673 0.2265 1.0000
8.000 1.2205 0.01116 0.00565 -0.0654 0.2204 1.0000
8.250 1.2379 0.01142 0.00589 -0.0635 0.2118 1.0000
8.500 1.2559 0.01168 0.00614 -0.0617 0.2024 1.0000
8.750 1.2726 0.01202 0.00643 -0.0598 0.1901 1.0000
9.000 1.2875 0.01244 0.00677 -0.0576 0.1717 1.0000
9.250 1.2980 0.01310 0.00726 -0.0547 0.1432 1.0000
9.500 1.3029 0.01407 0.00800 -0.0510 0.1075 1.0000
9.750 1.3082 0.01506 0.00881 -0.0475 0.0800 1.0000
10.000 1.3197 0.01577 0.00945 -0.0451 0.0685 1.0000
10.250 1.3342 0.01633 0.01001 -0.0432 0.0626 1.0000
10.500 1.3480 0.01694 0.01061 -0.0413 0.0583 1.0000
10.750 1.3632 0.01748 0.01118 -0.0396 0.0550 1.0000
11.000 1.3784 0.01804 0.01177 -0.0380 0.0524 1.0000
11.250 1.3915 0.01873 0.01246 -0.0362 0.0493 1.0000
11.500 1.4050 0.01941 0.01317 -0.0345 0.0468 1.0000
11.750 1.4206 0.01999 0.01379 -0.0331 0.0447 1.0000
12.000 1.4338 0.02072 0.01455 -0.0316 0.0424 1.0000
12.250 1.4444 0.02164 0.01548 -0.0297 0.0394 1.0000
12.500 1.4593 0.02230 0.01619 -0.0285 0.0377 1.0000
12.750 1.4713 0.02318 0.01709 -0.0270 0.0351 1.0000
13.000 1.4810 0.02422 0.01815 -0.0254 0.0323 1.0000
13.250 1.4923 0.02519 0.01915 -0.0241 0.0296 1.0000
13.500 1.4999 0.02645 0.02042 -0.0225 0.0269 1.0000
13.750 1.5080 0.02772 0.02171 -0.0211 0.0238 1.0000
14.000 1.5142 0.02918 0.02320 -0.0196 0.0217 1.0000
14.250 1.5200 0.03072 0.02478 -0.0183 0.0199 1.0000
14.500 1.5221 0.03263 0.02673 -0.0169 0.0183 1.0000
14.750 1.5277 0.03430 0.02849 -0.0159 0.0174 1.0000
15.000 1.5310 0.03626 0.03049 -0.0149 0.0165 1.0000
15.250 1.5322 0.03848 0.03278 -0.0140 0.0157 1.0000
15.500 1.5296 0.04116 0.03554 -0.0131 0.0149 1.0000
15.750 1.5324 0.04340 0.03786 -0.0126 0.0144 1.0000
16.000 1.5335 0.04589 0.04044 -0.0123 0.0140 1.0000
16.250 1.5326 0.04865 0.04327 -0.0120 0.0135 1.0000
16.500 1.5294 0.05176 0.04647 -0.0119 0.0131 1.0000
16.750 1.5208 0.05563 0.05042 -0.0120 0.0126 1.0000
17.000 1.5112 0.05976 0.05466 -0.0123 0.0123 1.0000
17.250 1.5003 0.06416 0.05918 -0.0129 0.0120 1.0000
17.500 1.4937 0.06814 0.06326 -0.0136 0.0119 1.0000
17.750 1.4873 0.07219 0.06742 -0.0144 0.0118 1.0000
18.000 1.4789 0.07658 0.07191 -0.0155 0.0116 1.0000
18.250 1.4678 0.08142 0.07687 -0.0167 0.0114 1.0000
18.500 1.4573 0.08628 0.08183 -0.0180 0.0112 1.0000
18.750 1.4462 0.09129 0.08694 -0.0195 0.0111 1.0000
19.000 1.4310 0.09696 0.09273 -0.0213 0.0110 1.0000
19.250 1.4198 0.10207 0.09792 -0.0230 0.0108 1.0000
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Polar data table (+)
Polar graphs
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