GOE 766 AIRFOIL (goe766-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 766 AIRFOIL (goe766-il) Reynolds number: 200,000 Max Cl/Cd: 55.9 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe766-il-200000.txt Download as CSV file: xf-goe766-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 766 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.5608 0.09468 0.09080 -0.0086 1.0000 0.0948
-10.000 -0.8562 0.04950 0.04410 -0.0259 1.0000 0.0588
-9.750 -0.8535 0.04550 0.03992 -0.0241 1.0000 0.0584
-9.500 -0.8529 0.04205 0.03615 -0.0216 1.0000 0.0583
-9.250 -0.8499 0.03915 0.03287 -0.0188 1.0000 0.0585
-9.000 -0.8445 0.03644 0.02977 -0.0161 1.0000 0.0591
-8.750 -0.8327 0.03348 0.02661 -0.0143 1.0000 0.0596
-8.500 -0.8173 0.03136 0.02433 -0.0126 1.0000 0.0602
-8.250 -0.8000 0.02966 0.02250 -0.0111 1.0000 0.0609
-8.000 -0.7811 0.02830 0.02105 -0.0096 1.0000 0.0619
-7.750 -0.7624 0.02707 0.01970 -0.0081 1.0000 0.0632
-7.500 -0.7436 0.02575 0.01819 -0.0064 1.0000 0.0645
-7.250 -0.7242 0.02446 0.01669 -0.0048 1.0000 0.0656
-7.000 -0.7039 0.02332 0.01536 -0.0032 1.0000 0.0665
-6.750 -0.6833 0.02240 0.01426 -0.0016 1.0000 0.0675
-6.500 -0.6614 0.02087 0.01278 -0.0006 1.0000 0.0695
-6.250 -0.6401 0.02008 0.01201 0.0007 1.0000 0.0714
-6.000 -0.6189 0.01932 0.01122 0.0021 1.0000 0.0734
-5.750 -0.5976 0.01859 0.01044 0.0036 1.0000 0.0753
-5.500 -0.5767 0.01798 0.00976 0.0051 1.0000 0.0771
-5.250 -0.5575 0.01700 0.00890 0.0067 1.0000 0.0802
-5.000 -0.5380 0.01648 0.00843 0.0084 1.0000 0.0837
-4.750 -0.5184 0.01601 0.00792 0.0101 1.0000 0.0873
-4.500 -0.5011 0.01532 0.00734 0.0121 1.0000 0.0915
-4.250 -0.4828 0.01492 0.00699 0.0139 1.0000 0.0972
-4.000 -0.4657 0.01446 0.00662 0.0159 1.0000 0.1046
-3.750 -0.4336 0.01400 0.00628 0.0148 0.9958 0.1191
-3.500 -0.3856 0.01332 0.00582 0.0107 0.9849 0.1564
-3.250 -0.3401 0.01254 0.00535 0.0069 0.9720 0.2060
-3.000 -0.2952 0.01170 0.00491 0.0034 0.9563 0.2731
-2.750 -0.2576 0.01060 0.00454 0.0014 0.9341 0.4221
-2.500 -0.2234 0.00971 0.00437 0.0006 0.9053 0.5847
-2.250 -0.1901 0.00934 0.00426 0.0006 0.8623 0.6772
-2.000 -0.1600 0.00921 0.00416 0.0015 0.8053 0.7344
-1.750 -0.1346 0.00928 0.00412 0.0033 0.7471 0.7843
-1.500 -0.1089 0.00950 0.00420 0.0050 0.6994 0.8250
-1.250 -0.0821 0.00976 0.00428 0.0062 0.6616 0.8555
-1.000 -0.0508 0.01003 0.00437 0.0063 0.6305 0.8763
-0.750 -0.0181 0.01031 0.00446 0.0060 0.6049 0.8937
-0.500 0.0171 0.01061 0.00459 0.0053 0.5823 0.9095
-0.250 0.0556 0.01096 0.00479 0.0039 0.5608 0.9247
0.000 0.1030 0.01136 0.00501 0.0006 0.5400 0.9351
0.250 0.1485 0.01167 0.00517 -0.0025 0.5216 0.9439
0.500 0.1872 0.01193 0.00529 -0.0043 0.5052 0.9550
0.750 0.2374 0.01218 0.00540 -0.0085 0.4873 0.9620
1.000 0.2800 0.01238 0.00547 -0.0114 0.4707 0.9715
1.250 0.3230 0.01251 0.00548 -0.0144 0.4548 0.9793
1.500 0.3672 0.01260 0.00545 -0.0178 0.4394 0.9865
1.750 0.4132 0.01268 0.00539 -0.0215 0.4241 0.9946
2.000 0.4535 0.01263 0.00529 -0.0243 0.4092 1.0000
2.250 0.4731 0.01268 0.00531 -0.0230 0.3978 1.0000
2.500 0.4931 0.01281 0.00533 -0.0217 0.3885 1.0000
2.750 0.5135 0.01287 0.00539 -0.0204 0.3781 1.0000
3.000 0.5343 0.01301 0.00546 -0.0192 0.3693 1.0000
3.250 0.5553 0.01310 0.00554 -0.0179 0.3600 1.0000
3.500 0.5765 0.01328 0.00566 -0.0167 0.3519 1.0000
3.750 0.5977 0.01339 0.00577 -0.0155 0.3431 1.0000
4.000 0.6191 0.01359 0.00592 -0.0142 0.3353 1.0000
4.250 0.6406 0.01373 0.00607 -0.0130 0.3271 1.0000
4.500 0.6622 0.01398 0.00624 -0.0118 0.3201 1.0000
4.750 0.6838 0.01414 0.00645 -0.0106 0.3121 1.0000
5.000 0.7055 0.01439 0.00661 -0.0094 0.3047 1.0000
5.250 0.7270 0.01452 0.00682 -0.0081 0.2959 1.0000
5.500 0.7487 0.01481 0.00700 -0.0069 0.2885 1.0000
5.750 0.7704 0.01497 0.00727 -0.0057 0.2803 1.0000
6.000 0.7921 0.01528 0.00747 -0.0045 0.2731 1.0000
6.250 0.8137 0.01547 0.00778 -0.0033 0.2649 1.0000
6.500 0.8353 0.01577 0.00801 -0.0021 0.2573 1.0000
6.750 0.8567 0.01598 0.00833 -0.0009 0.2486 1.0000
7.000 0.8779 0.01633 0.00857 0.0004 0.2403 1.0000
7.250 0.8990 0.01647 0.00887 0.0017 0.2304 1.0000
7.500 0.9197 0.01677 0.00916 0.0030 0.2208 1.0000
7.750 0.9401 0.01702 0.00941 0.0043 0.2100 1.0000
8.000 0.9605 0.01724 0.00973 0.0056 0.1974 1.0000
8.250 0.9804 0.01754 0.01006 0.0070 0.1834 1.0000
8.500 0.9994 0.01792 0.01042 0.0085 0.1680 1.0000
8.750 1.0172 0.01844 0.01088 0.0101 0.1525 1.0000
9.000 1.0335 0.01912 0.01149 0.0119 0.1387 1.0000
9.250 1.0493 0.01988 0.01223 0.0137 0.1273 1.0000
9.500 1.0642 0.02072 0.01306 0.0156 0.1184 1.0000
9.750 1.0767 0.02175 0.01397 0.0177 0.1115 1.0000
10.000 1.0925 0.02251 0.01484 0.0195 0.1056 1.0000
10.250 1.1052 0.02352 0.01578 0.0215 0.1009 1.0000
10.500 1.1189 0.02449 0.01682 0.0234 0.0968 1.0000
10.750 1.1325 0.02535 0.01773 0.0253 0.0930 1.0000
11.000 1.1445 0.02643 0.01877 0.0272 0.0897 1.0000
11.250 1.1569 0.02761 0.02001 0.0290 0.0870 1.0000
11.500 1.1683 0.02860 0.02112 0.0310 0.0845 1.0000
11.750 1.1776 0.02960 0.02216 0.0333 0.0821 1.0000
12.000 1.1871 0.03068 0.02323 0.0353 0.0800 1.0000
12.250 1.2000 0.03228 0.02480 0.0367 0.0777 1.0000
12.500 1.2042 0.03345 0.02615 0.0391 0.0763 1.0000
12.750 1.2091 0.03479 0.02765 0.0411 0.0747 1.0000
13.000 1.2143 0.03620 0.02916 0.0427 0.0731 1.0000
13.250 1.2212 0.03762 0.03063 0.0440 0.0714 1.0000
13.500 1.2327 0.03911 0.03209 0.0448 0.0698 1.0000
13.750 1.2406 0.04132 0.03437 0.0457 0.0684 1.0000
14.000 1.2364 0.04345 0.03673 0.0467 0.0675 1.0000
14.250 1.2319 0.04591 0.03939 0.0471 0.0665 1.0000
14.500 1.2280 0.04857 0.04222 0.0471 0.0655 1.0000
14.750 1.2233 0.05152 0.04533 0.0467 0.0645 1.0000
15.000 1.2196 0.05449 0.04844 0.0459 0.0635 1.0000
15.250 1.2189 0.05727 0.05129 0.0452 0.0625 1.0000
15.500 1.2229 0.05974 0.05378 0.0449 0.0614 1.0000
15.750 1.2274 0.06274 0.05679 0.0450 0.0602 1.0000
16.000 1.2077 0.06783 0.06212 0.0423 0.0599 1.0000
16.250 1.1824 0.07406 0.06859 0.0386 0.0596 1.0000
16.500 1.1555 0.08103 0.07580 0.0345 0.0595 1.0000
16.750 1.1209 0.08971 0.08471 0.0290 0.0595 1.0000
17.000 1.0744 0.10119 0.09644 0.0216 0.0597 1.0000
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