GOE 802 B AIRFOIL (goe802b-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 802 B AIRFOIL (goe802b-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.74 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe802b-il-1000000.txt Download as CSV file: xf-goe802b-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 802 B 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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.2665 0.08532 0.08365 -0.0421 0.9347 0.0172
-8.000 -0.2592 0.08256 0.08087 -0.0423 0.9240 0.0174
-7.750 -0.2492 0.07986 0.07812 -0.0439 0.9135 0.0175
-7.500 -0.2367 0.07710 0.07534 -0.0464 0.9035 0.0177
-7.250 -0.2228 0.07429 0.07248 -0.0492 0.8941 0.0179
-7.000 -0.2068 0.07125 0.06940 -0.0527 0.8850 0.0183
-6.750 -0.1894 0.06800 0.06609 -0.0565 0.8765 0.0189
-6.500 -0.1694 0.06447 0.06252 -0.0608 0.8676 0.0197
-6.250 -0.1384 0.05969 0.05758 -0.0689 0.8588 0.0206
-6.000 -0.1122 0.05553 0.05331 -0.0739 0.8498 0.0207
-5.750 -0.0876 0.05182 0.04946 -0.0772 0.8412 0.0208
-5.500 -0.0626 0.04809 0.04561 -0.0801 0.8327 0.0208
-5.250 -0.0461 0.04395 0.04138 -0.0817 0.8244 0.0212
-5.000 -0.0238 0.04180 0.03918 -0.0829 0.8159 0.0214
-4.750 -0.0001 0.03972 0.03699 -0.0840 0.8067 0.0217
-4.500 0.0251 0.03760 0.03477 -0.0853 0.7978 0.0221
-4.250 0.0511 0.03543 0.03246 -0.0864 0.7888 0.0228
-4.000 0.0789 0.03309 0.02998 -0.0875 0.7803 0.0239
-3.750 0.1122 0.03093 0.02747 -0.0881 0.7711 0.0249
-3.500 0.1394 0.02893 0.02529 -0.0885 0.7615 0.0250
-3.250 0.1628 0.02552 0.02169 -0.0894 0.7513 0.0255
-3.000 0.1888 0.02423 0.02032 -0.0898 0.7396 0.0259
-2.750 0.2152 0.02310 0.01907 -0.0901 0.7269 0.0264
-2.500 0.2422 0.02200 0.01781 -0.0903 0.7126 0.0273
-2.250 0.2725 0.02163 0.01715 -0.0898 0.6969 0.0297
-2.000 0.2996 0.01921 0.01443 -0.0900 0.6817 0.0302
-1.750 0.3263 0.01819 0.01329 -0.0902 0.6647 0.0306
-1.500 0.3533 0.01747 0.01244 -0.0904 0.6465 0.0310
-1.250 0.3806 0.01685 0.01169 -0.0905 0.6284 0.0318
-1.000 0.4085 0.01627 0.01095 -0.0905 0.6111 0.0336
-0.750 0.4375 0.01618 0.01065 -0.0901 0.5954 0.0352
0.250 0.5466 0.00987 0.00343 -0.0901 0.5444 0.0305
0.500 0.5739 0.00958 0.00309 -0.0901 0.5330 0.0305
0.750 0.6012 0.00937 0.00284 -0.0901 0.5210 0.0305
1.000 0.6289 0.00920 0.00265 -0.0901 0.5099 0.0309
1.250 0.6566 0.00913 0.00255 -0.0901 0.4979 0.0316
1.500 0.6843 0.00914 0.00250 -0.0901 0.4838 0.0326
1.750 0.7121 0.00916 0.00248 -0.0901 0.4691 0.0337
2.000 0.7399 0.00922 0.00249 -0.0901 0.4556 0.0348
2.250 0.7678 0.00932 0.00255 -0.0901 0.4436 0.0359
2.500 0.7954 0.00945 0.00264 -0.0901 0.4303 0.0386
2.750 0.8233 0.00964 0.00286 -0.0900 0.4166 0.0475
3.000 0.8512 0.01000 0.00315 -0.0900 0.4034 0.0659
3.250 0.8788 0.01038 0.00345 -0.0900 0.3915 0.0720
3.500 0.9064 0.01053 0.00357 -0.0900 0.3811 0.0758
3.750 0.9338 0.01107 0.00403 -0.0899 0.3703 0.0818
4.000 0.9602 0.01079 0.00374 -0.0899 0.3578 0.0827
4.250 0.9873 0.01099 0.00391 -0.0898 0.3472 0.0861
4.500 1.0141 0.01129 0.00416 -0.0897 0.3390 0.0863
4.750 1.0410 0.01137 0.00424 -0.0897 0.3316 0.0864
5.000 1.0673 0.01114 0.00404 -0.0897 0.3236 0.0867
5.250 1.0943 0.01103 0.00399 -0.0897 0.3172 0.0872
5.500 1.1205 0.01109 0.00405 -0.0896 0.3086 0.0880
5.750 1.1471 0.01115 0.00413 -0.0896 0.2998 0.0891
6.250 1.1993 0.01167 0.00458 -0.0893 0.2808 0.0911
6.500 1.2250 0.01162 0.00456 -0.0892 0.2678 0.0918
6.750 1.2498 0.01182 0.00470 -0.0890 0.2478 0.0931
7.000 1.2734 0.01227 0.00502 -0.0885 0.2240 0.0956
7.250 1.2965 0.01261 0.00525 -0.0880 0.1978 0.0971
7.750 1.3418 0.01348 0.00595 -0.0869 0.1604 0.1025
8.250 1.3887 0.01416 0.00658 -0.0859 0.1412 0.1105
8.500 1.4122 0.01442 0.00684 -0.0854 0.1323 0.1170
10.000 1.5323 0.01756 0.00960 -0.0796 0.0604 0.1558
10.250 1.5489 0.01821 0.01023 -0.0782 0.0532 0.1580
10.500 1.5653 0.01883 0.01084 -0.0766 0.0455 0.1611
10.750 1.5655 0.02009 0.01194 -0.0725 0.0225 0.1631
11.000 1.5723 0.02116 0.01302 -0.0696 0.0172 0.1657
11.250 1.5836 0.02201 0.01395 -0.0675 0.0154 0.1785
11.500 1.5965 0.02278 0.01482 -0.0658 0.0148 0.1929
11.750 1.6077 0.02368 0.01580 -0.0640 0.0141 0.1977
12.000 1.6174 0.02474 0.01694 -0.0621 0.0136 0.2014
12.250 1.6251 0.02597 0.01826 -0.0602 0.0130 0.2067
12.500 1.6307 0.02743 0.01981 -0.0582 0.0125 0.2030
12.750 1.6354 0.02902 0.02149 -0.0563 0.0121 0.1976
13.000 1.6438 0.03037 0.02291 -0.0550 0.0119 0.1763
13.250 1.6508 0.03189 0.02450 -0.0536 0.0117 0.1664
13.500 1.6567 0.03356 0.02626 -0.0524 0.0114 0.1661
13.750 1.6615 0.03541 0.02819 -0.0513 0.0111 0.1650
14.000 1.6646 0.03747 0.03034 -0.0502 0.0108 0.1649
14.250 1.6662 0.03978 0.03274 -0.0493 0.0105 0.1662
14.500 1.6663 0.04234 0.03540 -0.0486 0.0103 0.1679
14.750 1.6641 0.04524 0.03841 -0.0480 0.0101 0.1685
15.000 1.6592 0.04859 0.04186 -0.0476 0.0099 0.1660
15.250 1.6516 0.05243 0.04582 -0.0476 0.0098 0.1653
15.500 1.6402 0.05694 0.05046 -0.0478 0.0096 0.1642
15.750 1.6255 0.06213 0.05579 -0.0485 0.0095 0.1640
16.000 1.6083 0.06782 0.06162 -0.0495 0.0094 0.1638
16.250 1.5959 0.07297 0.06689 -0.0505 0.0093 0.1634
16.500 1.5886 0.07746 0.07149 -0.0515 0.0092 0.1628
16.750 1.5786 0.08240 0.07653 -0.0527 0.0092 0.1627
17.000 1.5677 0.08753 0.08178 -0.0540 0.0091 0.1629
17.250 1.5564 0.09284 0.08719 -0.0555 0.0091 0.1626
17.500 1.5444 0.09830 0.09277 -0.0572 0.0090 0.1628
17.750 1.5314 0.10399 0.09857 -0.0590 0.0090 0.1617
18.000 1.5192 0.10965 0.10433 -0.0609 0.0089 0.1624
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Polar data table (+)
Polar graphs
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