GOE 780 AIRFOIL (goe780-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 780 AIRFOIL (goe780-il) Reynolds number: 1,000,000 Max Cl/Cd: 50.86 at α=2.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe780-il-1000000.txt Download as CSV file: xf-goe780-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 780 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.4769 0.10230 0.10074 -0.0435 1.0000 0.0069
-11.000 -0.4796 0.09730 0.09576 -0.0457 1.0000 0.0069
-10.750 -0.4855 0.09323 0.09173 -0.0461 0.9932 0.0069
-10.500 -0.4759 0.08558 0.08406 -0.0547 0.9709 0.0069
-10.250 -0.4639 0.07472 0.07315 -0.0701 0.9578 0.0069
-10.000 -0.4553 0.06468 0.06292 -0.0842 0.9438 0.0069
-9.750 -0.4514 0.05702 0.05494 -0.0924 0.9050 0.0070
-9.500 -0.4641 0.05424 0.05186 -0.0898 0.8640 0.0070
-7.000 -0.5449 0.02233 0.01747 -0.0382 0.8040 0.0067
-6.750 -0.5292 0.01963 0.01441 -0.0359 0.8015 0.0068
-6.500 -0.5074 0.01723 0.01166 -0.0349 0.7991 0.0073
-6.250 -0.4813 0.01588 0.01013 -0.0348 0.7969 0.0072
-6.000 -0.4504 0.01307 0.00701 -0.0358 0.7949 0.0076
-5.750 -0.4278 0.01232 0.00616 -0.0351 0.7924 0.0089
-5.500 -0.4062 0.01175 0.00553 -0.0341 0.7904 0.0094
-5.250 -0.3853 0.01127 0.00499 -0.0329 0.7882 0.0102
-5.000 -0.3642 0.01089 0.00455 -0.0317 0.7859 0.0113
-4.750 -0.3408 0.01077 0.00441 -0.0310 0.7836 0.0119
-4.500 -0.3242 0.01001 0.00353 -0.0288 0.7813 0.0159
-4.250 -0.3018 0.00979 0.00324 -0.0279 0.7791 0.0183
-4.000 -0.2801 0.00949 0.00295 -0.0267 0.7771 0.0268
-3.750 -0.2567 0.00933 0.00280 -0.0261 0.7752 0.0341
-3.500 -0.2331 0.00919 0.00266 -0.0255 0.7730 0.0404
-3.250 -0.2088 0.00909 0.00253 -0.0250 0.7708 0.0425
-3.000 -0.1856 0.00890 0.00229 -0.0242 0.7688 0.0484
-2.750 -0.1624 0.00873 0.00212 -0.0235 0.7669 0.0593
-2.500 -0.1418 0.00842 0.00200 -0.0223 0.7647 0.1200
-2.250 -0.1316 0.00757 0.00179 -0.0191 0.7627 0.2958
-2.000 -0.1263 0.00668 0.00158 -0.0147 0.7603 0.4828
-1.750 -0.1315 0.00588 0.00143 -0.0077 0.7577 0.6612
-1.500 -0.1254 0.00547 0.00133 -0.0028 0.7554 0.7428
-1.250 -0.1151 0.00524 0.00144 0.0013 0.7533 0.8392
-1.000 -0.0932 0.00529 0.00151 0.0026 0.7513 0.8645
-0.750 -0.0692 0.00533 0.00156 0.0033 0.7495 0.8783
-0.500 -0.0458 0.00536 0.00160 0.0042 0.7475 0.8887
-0.250 -0.0148 0.00539 0.00165 0.0034 0.7451 0.8969
0.000 0.0120 0.00542 0.00168 0.0035 0.7414 0.9065
0.250 0.0433 0.00552 0.00177 0.0026 0.7392 0.9138
0.500 0.0721 0.00560 0.00184 0.0022 0.7366 0.9193
0.750 0.1119 0.00571 0.00199 -0.0006 0.7322 0.9235
1.000 0.1412 0.00573 0.00201 -0.0012 0.7286 0.9261
1.250 0.1605 0.00572 0.00199 0.0006 0.7257 0.9298
1.500 0.1906 0.00575 0.00203 -0.0002 0.7223 0.9318
1.750 0.2218 0.00571 0.00197 -0.0011 0.7087 0.9330
2.000 0.2538 0.00572 0.00199 -0.0022 0.6916 0.9342
2.250 0.2846 0.00578 0.00203 -0.0031 0.6727 0.9355
2.500 0.3072 0.00604 0.00207 -0.0022 0.6052 0.9377
2.750 0.2914 0.00727 0.00246 0.0068 0.3925 0.9452
3.000 0.2960 0.00936 0.00330 0.0103 0.0433 0.9480
3.250 0.3259 0.00980 0.00367 0.0094 0.0170 0.9495
3.500 0.3529 0.01020 0.00419 0.0094 0.0140 0.9514
3.750 0.3573 0.01033 0.00435 0.0144 0.0135 0.9575
4.000 0.3928 0.01080 0.00486 0.0122 0.0124 0.9582
4.250 0.4197 0.01131 0.00543 0.0120 0.0116 0.9590
4.500 0.4453 0.01186 0.00605 0.0120 0.0107 0.9599
4.750 0.4696 0.01245 0.00669 0.0121 0.0097 0.9611
5.000 0.4867 0.01354 0.00781 0.0137 0.0085 0.9634
5.250 0.5032 0.01445 0.00879 0.0158 0.0085 0.9665
5.500 0.5544 0.02005 0.01471 0.0121 0.0138 0.9619
5.750 0.5821 0.02124 0.01606 0.0120 0.0137 0.9629
6.000 0.6044 0.02004 0.01489 0.0128 0.0117 0.9657
6.250 0.6148 0.01995 0.01480 0.0158 0.0097 0.9707
6.500 0.6451 0.02174 0.01676 0.0150 0.0095 0.9710
6.750 0.6707 0.02345 0.01850 0.0142 0.0083 0.9714
7.000 0.6823 0.03111 0.02684 0.0173 0.0077 0.9723
7.250 0.7000 0.03395 0.02995 0.0185 0.0077 0.9736
7.500 0.7154 0.03698 0.03326 0.0202 0.0077 0.9754
7.750 0.7293 0.03988 0.03641 0.0221 0.0076 0.9778
8.000 0.7513 0.04132 0.03798 0.0235 0.0071 0.9801
8.250 0.7630 0.04386 0.04071 0.0265 0.0064 0.9835
8.500 0.7767 0.04750 0.04457 0.0276 0.0060 0.9846
8.750 0.7867 0.05105 0.04834 0.0286 0.0056 0.9861
9.000 0.7929 0.05457 0.05204 0.0298 0.0054 0.9883
9.250 0.7955 0.05822 0.05585 0.0311 0.0053 0.9914
9.500 0.7923 0.06212 0.05991 0.0329 0.0053 0.9949
9.750 0.7857 0.06531 0.06324 0.0340 0.0051 0.9973
10.000 0.7753 0.06903 0.06709 0.0346 0.0051 0.9993
10.250 0.7551 0.07269 0.07085 0.0367 0.0053 1.0000
10.500 0.7315 0.07539 0.07361 0.0397 0.0052 1.0000
10.750 0.7091 0.07869 0.07696 0.0415 0.0051 1.0000
11.000 0.6842 0.08355 0.08188 0.0417 0.0052 1.0000
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Polar data table (+)
Polar graphs
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