GOE 548 AIRFOIL (goe548-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 548 AIRFOIL (goe548-il) Reynolds number: 1,000,000 Max Cl/Cd: 100.74 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe548-il-1000000.txt Download as CSV file: xf-goe548-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 548 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
------ -------- --------- --------- -------- -------- --------
-13.750 -0.6942 0.08203 0.08030 -0.0539 1.0000 0.0074
-13.500 -0.8405 0.04954 0.04722 -0.0748 1.0000 0.0066
-13.250 -0.8607 0.04386 0.04139 -0.0780 1.0000 0.0066
-13.000 -0.8854 0.03919 0.03656 -0.0789 1.0000 0.0066
-12.500 -0.8934 0.03438 0.03155 -0.0794 0.9982 0.0068
-12.250 -0.8917 0.03075 0.02763 -0.0816 0.9947 0.0068
-12.000 -0.8827 0.02883 0.02554 -0.0815 0.9904 0.0069
-11.750 -0.8680 0.02700 0.02352 -0.0818 0.9867 0.0070
-11.500 -0.8476 0.02512 0.02144 -0.0829 0.9846 0.0072
-11.250 -0.8289 0.02400 0.02020 -0.0827 0.9811 0.0074
-11.000 -0.8118 0.02249 0.01850 -0.0822 0.9772 0.0076
-10.750 -0.7891 0.02131 0.01718 -0.0826 0.9751 0.0079
-10.500 -0.7652 0.02010 0.01581 -0.0830 0.9735 0.0081
-10.250 -0.7392 0.01909 0.01467 -0.0837 0.9724 0.0083
-10.000 -0.7110 0.01832 0.01378 -0.0846 0.9715 0.0085
-9.750 -0.6999 0.01669 0.01192 -0.0824 0.9656 0.0090
-9.500 -0.6752 0.01569 0.01085 -0.0826 0.9634 0.0097
-9.250 -0.6463 0.01511 0.01021 -0.0835 0.9619 0.0102
-9.000 -0.6165 0.01449 0.00952 -0.0845 0.9607 0.0107
-8.750 -0.5861 0.01385 0.00879 -0.0856 0.9594 0.0113
-8.500 -0.5561 0.01329 0.00815 -0.0865 0.9577 0.0117
-8.250 -0.5365 0.01259 0.00734 -0.0852 0.9533 0.0123
-8.000 -0.5119 0.01192 0.00661 -0.0850 0.9503 0.0135
-7.750 -0.4825 0.01154 0.00619 -0.0857 0.9481 0.0147
-7.500 -0.4515 0.01117 0.00577 -0.0867 0.9460 0.0158
-7.250 -0.4260 0.01067 0.00522 -0.0865 0.9428 0.0178
-7.000 -0.4015 0.01042 0.00496 -0.0860 0.9391 0.0199
-6.750 -0.3746 0.01016 0.00466 -0.0860 0.9359 0.0221
-6.500 -0.3461 0.00985 0.00438 -0.0864 0.9331 0.0266
-6.250 -0.3153 0.00971 0.00420 -0.0872 0.9307 0.0295
-6.000 -0.2929 0.00947 0.00400 -0.0862 0.9270 0.0339
-5.750 -0.2665 0.00937 0.00388 -0.0860 0.9237 0.0366
-5.500 -0.2383 0.00930 0.00378 -0.0862 0.9204 0.0379
-5.250 -0.2112 0.00893 0.00335 -0.0862 0.9168 0.0425
-5.000 -0.1881 0.00876 0.00317 -0.0853 0.9124 0.0454
-4.750 -0.1626 0.00860 0.00297 -0.0848 0.9073 0.0477
-4.250 -0.1119 0.00826 0.00255 -0.0838 0.8960 0.0547
-4.000 -0.0865 0.00806 0.00233 -0.0833 0.8904 0.0601
-3.750 -0.0615 0.00787 0.00215 -0.0828 0.8853 0.0711
-3.500 -0.0422 0.00732 0.00192 -0.0812 0.8792 0.1494
-3.250 -0.0188 0.00693 0.00176 -0.0805 0.8738 0.2218
-3.000 0.0025 0.00664 0.00164 -0.0792 0.8670 0.2713
-2.750 0.0261 0.00636 0.00152 -0.0784 0.8605 0.3250
-2.500 0.0487 0.00613 0.00143 -0.0774 0.8525 0.3742
-2.250 0.0730 0.00595 0.00134 -0.0767 0.8443 0.4129
-2.000 0.0959 0.00577 0.00126 -0.0757 0.8328 0.4520
-1.750 0.1188 0.00560 0.00119 -0.0746 0.8190 0.4941
-1.500 0.1412 0.00546 0.00112 -0.0734 0.8016 0.5373
-1.250 0.1630 0.00540 0.00106 -0.0721 0.7801 0.5721
-1.000 0.1848 0.00539 0.00103 -0.0708 0.7616 0.6025
-0.500 0.2296 0.00535 0.00105 -0.0684 0.7348 0.6655
-0.250 0.2512 0.00527 0.00108 -0.0670 0.7255 0.7136
0.000 0.2731 0.00524 0.00111 -0.0657 0.7154 0.7518
0.250 0.2960 0.00521 0.00115 -0.0645 0.7062 0.7841
0.500 0.3199 0.00519 0.00119 -0.0636 0.6990 0.8114
1.000 0.3689 0.00518 0.00128 -0.0621 0.6846 0.8593
1.250 0.3943 0.00517 0.00133 -0.0614 0.6760 0.8850
1.500 0.4229 0.00518 0.00140 -0.0616 0.6663 0.9120
1.750 0.4599 0.00525 0.00150 -0.0636 0.6542 0.9350
2.000 0.4992 0.00536 0.00159 -0.0662 0.6412 0.9482
2.250 0.5346 0.00548 0.00168 -0.0680 0.6235 0.9572
2.500 0.5702 0.00566 0.00177 -0.0698 0.5949 0.9634
2.750 0.5975 0.00599 0.00190 -0.0699 0.5491 0.9712
3.000 0.6274 0.00644 0.00211 -0.0706 0.4981 0.9763
3.250 0.6544 0.00679 0.00230 -0.0706 0.4588 0.9831
3.500 0.6885 0.00716 0.00248 -0.0723 0.4154 0.9860
3.750 0.7181 0.00778 0.00276 -0.0732 0.3394 0.9903
4.000 0.7412 0.00896 0.00328 -0.0732 0.2026 0.9954
4.250 0.7750 0.00954 0.00360 -0.0750 0.1514 0.9985
4.500 0.7983 0.01017 0.00392 -0.0747 0.0916 1.0000
4.750 0.8115 0.01048 0.00415 -0.0718 0.0750 1.0000
5.000 0.8182 0.01111 0.00453 -0.0677 0.0240 1.0000
5.250 0.8328 0.01142 0.00485 -0.0650 0.0179 1.0000
5.500 0.8495 0.01165 0.00511 -0.0628 0.0168 1.0000
5.750 0.8657 0.01192 0.00540 -0.0605 0.0155 1.0000
6.000 0.8811 0.01224 0.00576 -0.0580 0.0146 1.0000
6.250 0.8930 0.01275 0.00633 -0.0548 0.0130 1.0000
6.500 0.9051 0.01317 0.00680 -0.0517 0.0127 1.0000
6.750 0.9192 0.01345 0.00710 -0.0490 0.0122 1.0000
7.000 0.9327 0.01378 0.00747 -0.0462 0.0116 1.0000
7.250 0.9452 0.01422 0.00796 -0.0432 0.0114 1.0000
7.500 0.9593 0.01464 0.00841 -0.0407 0.0107 1.0000
7.750 0.9722 0.01516 0.00896 -0.0380 0.0103 1.0000
8.000 0.9864 0.01563 0.00946 -0.0357 0.0098 1.0000
8.250 0.9905 0.01671 0.01060 -0.0317 0.0092 1.0000
8.500 0.9956 0.01783 0.01179 -0.0279 0.0089 1.0000
8.750 1.0120 0.01829 0.01230 -0.0262 0.0087 1.0000
9.000 1.0253 0.01898 0.01305 -0.0240 0.0086 1.0000
9.250 1.0390 0.01969 0.01380 -0.0219 0.0082 1.0000
9.500 1.0516 0.02050 0.01467 -0.0197 0.0080 1.0000
9.750 1.0632 0.02146 0.01569 -0.0175 0.0079 1.0000
10.000 1.0766 0.02227 0.01656 -0.0156 0.0077 1.0000
10.250 1.0882 0.02336 0.01770 -0.0136 0.0075 1.0000
10.500 1.1014 0.02421 0.01860 -0.0118 0.0072 1.0000
10.750 1.1136 0.02517 0.01963 -0.0101 0.0070 1.0000
11.000 1.1253 0.02612 0.02062 -0.0084 0.0067 1.0000
11.250 1.1362 0.02748 0.02206 -0.0065 0.0067 1.0000
11.500 1.1471 0.02890 0.02355 -0.0047 0.0066 1.0000
11.750 1.1602 0.03276 0.02758 -0.0033 0.0062 1.0000
12.000 1.1653 0.03383 0.02876 -0.0010 0.0061 1.0000
12.250 1.1692 0.03442 0.02947 0.0011 0.0059 1.0000
12.500 1.1737 0.03660 0.03182 0.0032 0.0059 1.0000
12.750 1.1770 0.03846 0.03382 0.0051 0.0058 1.0000
13.000 1.1780 0.04055 0.03607 0.0070 0.0057 1.0000
13.250 1.1742 0.04346 0.03916 0.0090 0.0058 1.0000
13.500 1.1674 0.04662 0.04251 0.0109 0.0059 1.0000
13.750 1.1620 0.04924 0.04530 0.0122 0.0057 1.0000
14.000 1.1502 0.05295 0.04921 0.0133 0.0057 1.0000
14.250 1.1383 0.05676 0.05319 0.0140 0.0057 1.0000
14.500 1.1226 0.06120 0.05781 0.0141 0.0057 1.0000
14.750 1.1126 0.06508 0.06185 0.0137 0.0056 1.0000
15.000 1.0988 0.06977 0.06670 0.0127 0.0055 1.0000
15.250 1.0717 0.07687 0.07398 0.0108 0.0058 1.0000
15.500 1.0613 0.08186 0.07911 0.0086 0.0056 1.0000
16.000 1.0133 0.09754 0.09508 0.0011 0.0059 1.0000
16.250 0.9945 0.10545 0.10314 -0.0034 0.0059 1.0000
16.500 0.9769 0.11360 0.11142 -0.0083 0.0058 1.0000
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Polar data table (+)
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