GOE 670 AIRFOIL (goe670-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 670 AIRFOIL (goe670-il) Reynolds number: 200,000 Max Cl/Cd: 78.42 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe670-il-200000.txt Download as CSV file: xf-goe670-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 670 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.4073 0.09516 0.09164 -0.0337 1.0000 0.0616
-8.500 -0.4031 0.09320 0.08969 -0.0312 1.0000 0.0629
-8.250 -0.4087 0.09130 0.08784 -0.0293 1.0000 0.0640
-8.000 -0.4187 0.08949 0.08608 -0.0273 1.0000 0.0650
-7.750 -0.4334 0.08783 0.08449 -0.0249 1.0000 0.0658
-7.500 -0.4525 0.08635 0.08307 -0.0222 1.0000 0.0664
-7.250 -0.4671 0.08406 0.08083 -0.0214 1.0000 0.0678
-7.000 -0.4789 0.08111 0.07789 -0.0226 1.0000 0.0695
-6.750 -0.4954 0.07612 0.07264 -0.0318 1.0000 0.0716
-6.500 -0.4863 0.07016 0.06675 -0.0320 0.9981 0.0726
-6.250 -0.4658 0.06767 0.06430 -0.0317 0.9954 0.0739
-6.000 -0.4428 0.06513 0.06173 -0.0333 0.9919 0.0764
-5.750 -0.4082 0.05738 0.05329 -0.0464 0.9846 0.0850
-5.500 -0.3877 0.05353 0.04956 -0.0472 0.9814 0.0862
-5.250 -0.3661 0.05109 0.04713 -0.0479 0.9767 0.0877
-5.000 -0.3379 0.04860 0.04457 -0.0501 0.9729 0.0911
-4.750 -0.3092 0.04377 0.03912 -0.0542 0.9671 0.1001
-4.500 -0.2898 0.03300 0.02739 -0.0549 0.9619 0.0733
-4.250 -0.2574 0.02974 0.02372 -0.0563 0.9586 0.0698
-4.000 -0.2249 0.02689 0.02041 -0.0576 0.9554 0.0698
-3.750 -0.2013 0.02474 0.01789 -0.0569 0.9487 0.0698
-3.500 -0.1670 0.02295 0.01569 -0.0581 0.9450 0.0705
-3.250 -0.1291 0.02157 0.01396 -0.0600 0.9425 0.0720
-3.000 -0.1038 0.02050 0.01287 -0.0597 0.9359 0.0748
-2.750 -0.0688 0.01991 0.01221 -0.0611 0.9311 0.0785
-2.500 -0.0286 0.01911 0.01124 -0.0633 0.9283 0.0825
-2.250 0.0006 0.01832 0.01038 -0.0634 0.9219 0.0865
-2.000 0.0350 0.01786 0.00996 -0.0647 0.9166 0.0935
-1.750 0.0751 0.01721 0.00932 -0.0670 0.9138 0.1037
-1.500 0.1070 0.01676 0.00885 -0.0676 0.9077 0.1149
-1.250 0.1411 0.01630 0.00843 -0.0687 0.9019 0.1291
-1.000 0.1830 0.01556 0.00784 -0.0714 0.8990 0.1478
-0.750 0.2301 0.01485 0.00725 -0.0750 0.8969 0.1688
-0.500 0.2572 0.01436 0.00685 -0.0744 0.8862 0.1875
-0.250 0.3014 0.01352 0.00622 -0.0771 0.8823 0.2239
0.000 0.4388 0.01097 0.00591 -0.0993 0.8874 1.0000
0.250 0.4726 0.01063 0.00547 -0.0999 0.8777 1.0000
0.500 0.5043 0.01034 0.00508 -0.1000 0.8674 1.0000
0.750 0.5281 0.01020 0.00488 -0.0988 0.8545 1.0000
1.000 0.5527 0.01010 0.00471 -0.0977 0.8421 1.0000
1.250 0.5782 0.00999 0.00456 -0.0968 0.8296 1.0000
1.500 0.6037 0.00991 0.00441 -0.0959 0.8167 1.0000
1.750 0.6288 0.00985 0.00430 -0.0950 0.8032 1.0000
2.000 0.6529 0.00983 0.00423 -0.0939 0.7887 1.0000
2.250 0.6761 0.00983 0.00419 -0.0926 0.7726 1.0000
2.500 0.6990 0.00984 0.00415 -0.0913 0.7550 1.0000
2.750 0.7222 0.00987 0.00413 -0.0899 0.7363 1.0000
3.000 0.7458 0.00992 0.00410 -0.0887 0.7170 1.0000
3.250 0.7682 0.01002 0.00413 -0.0873 0.6962 1.0000
3.500 0.7907 0.01016 0.00417 -0.0858 0.6741 1.0000
3.750 0.8123 0.01036 0.00428 -0.0843 0.6506 1.0000
4.000 0.8328 0.01062 0.00440 -0.0825 0.6235 1.0000
4.250 0.8508 0.01090 0.00457 -0.0802 0.5907 1.0000
4.500 0.8664 0.01120 0.00474 -0.0774 0.5466 1.0000
4.750 0.8777 0.01162 0.00489 -0.0739 0.4778 1.0000
5.000 0.8856 0.01235 0.00519 -0.0699 0.4135 1.0000
5.250 0.8983 0.01303 0.00560 -0.0670 0.3729 1.0000
5.500 0.9143 0.01362 0.00602 -0.0647 0.3472 1.0000
5.750 0.9324 0.01414 0.00645 -0.0629 0.3280 1.0000
6.000 0.9513 0.01463 0.00686 -0.0612 0.3127 1.0000
6.250 0.9702 0.01509 0.00726 -0.0596 0.2978 1.0000
6.500 0.9890 0.01554 0.00766 -0.0579 0.2832 1.0000
6.750 1.0078 0.01598 0.00808 -0.0563 0.2699 1.0000
7.000 1.0265 0.01644 0.00850 -0.0547 0.2578 1.0000
7.250 1.0454 0.01686 0.00893 -0.0532 0.2466 1.0000
7.500 1.0643 0.01721 0.00934 -0.0516 0.2345 1.0000
7.750 1.0818 0.01757 0.00975 -0.0498 0.2204 1.0000
8.000 1.0992 0.01792 0.01014 -0.0480 0.2061 1.0000
8.250 1.1144 0.01828 0.01050 -0.0458 0.1861 1.0000
8.500 1.1273 0.01875 0.01082 -0.0432 0.1322 1.0000
8.750 1.1253 0.02059 0.01206 -0.0386 0.0679 1.0000
9.000 1.1336 0.02176 0.01315 -0.0355 0.0523 1.0000
9.250 1.1412 0.02291 0.01428 -0.0324 0.0458 1.0000
9.500 1.1507 0.02390 0.01536 -0.0296 0.0421 1.0000
9.750 1.1570 0.02509 0.01660 -0.0266 0.0398 1.0000
10.000 1.1578 0.02670 0.01824 -0.0230 0.0380 1.0000
10.250 1.1659 0.02795 0.01958 -0.0205 0.0367 1.0000
10.500 1.1741 0.02929 0.02102 -0.0180 0.0356 1.0000
10.750 1.1826 0.03067 0.02249 -0.0158 0.0341 1.0000
11.000 1.1909 0.03215 0.02401 -0.0138 0.0328 1.0000
11.250 1.1993 0.03404 0.02589 -0.0119 0.0312 1.0000
11.500 1.2173 0.03644 0.02831 -0.0109 0.0303 1.0000
11.750 1.2309 0.03798 0.03001 -0.0094 0.0298 1.0000
12.000 1.2444 0.03976 0.03196 -0.0080 0.0294 1.0000
12.250 1.2575 0.04178 0.03418 -0.0066 0.0290 1.0000
12.500 1.2665 0.04396 0.03658 -0.0049 0.0286 1.0000
12.750 1.2714 0.04614 0.03898 -0.0031 0.0281 1.0000
13.000 1.2735 0.04850 0.04155 -0.0013 0.0275 1.0000
13.250 1.2738 0.05090 0.04414 0.0004 0.0269 1.0000
13.500 1.2735 0.05346 0.04687 0.0019 0.0263 1.0000
13.750 1.2686 0.05655 0.05019 0.0034 0.0262 1.0000
14.000 1.2586 0.06017 0.05408 0.0047 0.0263 1.0000
14.250 1.2455 0.06410 0.05827 0.0054 0.0264 1.0000
14.500 1.2295 0.06852 0.06295 0.0056 0.0265 1.0000
14.750 1.2083 0.07383 0.06855 0.0049 0.0269 1.0000
15.000 1.1874 0.07945 0.07441 0.0034 0.0269 1.0000
15.250 1.1636 0.08597 0.08118 0.0008 0.0273 1.0000
15.500 1.1394 0.09311 0.08854 -0.0026 0.0276 1.0000
15.750 1.1122 0.10157 0.09722 -0.0074 0.0280 1.0000
16.000 1.0851 0.11083 0.10667 -0.0133 0.0283 1.0000
16.250 1.0556 0.12162 0.11763 -0.0203 0.0287 1.0000
16.500 1.0244 0.13386 0.13001 -0.0283 0.0293 1.0000
16.750 1.0023 0.14424 0.14043 -0.0341 0.0301 1.0000
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