GOE 795 AIRFOIL (goe795-il) Xfoil prediction polar at RE=100,000 Ncrit=9
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Airfoil: GOE 795 AIRFOIL (goe795-il) Reynolds number: 100,000 Max Cl/Cd: 56.51 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe795-il-100000.txt Download as CSV file: xf-goe795-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 795 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.4467 0.11477 0.10959 -0.0217 1.0000 0.0876
-9.750 -0.4578 0.11301 0.10792 -0.0255 1.0000 0.0896
-9.500 -0.4723 0.11129 0.10632 -0.0296 1.0000 0.0901
-9.250 -0.4445 0.10447 0.09943 -0.0245 1.0000 0.0936
-9.000 -0.4384 0.10148 0.09646 -0.0242 1.0000 0.0984
-8.750 -0.4474 0.09912 0.09418 -0.0268 1.0000 0.1024
-8.500 -0.4662 0.09719 0.09240 -0.0303 1.0000 0.1035
-8.250 -0.4523 0.09216 0.08736 -0.0279 1.0000 0.1065
-8.000 -0.4447 0.08908 0.08426 -0.0266 1.0000 0.1096
-7.750 -0.4493 0.08635 0.08160 -0.0266 1.0000 0.1127
-7.500 -0.4636 0.08368 0.07904 -0.0287 1.0000 0.1159
-7.250 -0.4878 0.08018 0.07558 -0.0367 1.0000 0.1183
-7.000 -0.4711 0.07626 0.07171 -0.0311 1.0000 0.1204
-6.750 -0.4649 0.07343 0.06890 -0.0292 1.0000 0.1236
-6.500 -0.4710 0.07024 0.06564 -0.0330 1.0000 0.1307
-6.250 -0.4239 0.05653 0.05239 -0.0282 1.0000 0.1352
-6.000 -0.4232 0.05358 0.04946 -0.0267 1.0000 0.1388
-5.750 -0.4640 0.06019 0.05537 -0.0330 1.0000 0.1463
-5.500 -0.4550 0.05700 0.05229 -0.0302 1.0000 0.1485
-5.250 -0.4467 0.05440 0.04966 -0.0287 1.0000 0.1532
-5.000 -0.4401 0.05129 0.04641 -0.0285 1.0000 0.1624
-4.750 -0.4200 0.03645 0.02990 -0.0315 1.0000 0.0749
-4.500 -0.4060 0.03312 0.02626 -0.0299 1.0000 0.0721
-4.250 -0.3900 0.02974 0.02235 -0.0282 1.0000 0.0693
-4.000 -0.3719 0.02704 0.01909 -0.0264 1.0000 0.0683
-3.750 -0.3532 0.02561 0.01734 -0.0249 1.0000 0.0720
-3.500 -0.3331 0.02434 0.01556 -0.0232 1.0000 0.0762
-3.250 -0.3126 0.02256 0.01360 -0.0219 1.0000 0.0797
-3.000 -0.2922 0.02150 0.01236 -0.0206 1.0000 0.0857
-2.750 -0.2718 0.02033 0.01107 -0.0191 1.0000 0.0965
-2.500 -0.2523 0.01952 0.01022 -0.0178 1.0000 0.1114
-2.250 -0.2339 0.01902 0.00970 -0.0165 1.0000 0.1334
-2.000 -0.2154 0.01852 0.00931 -0.0152 1.0000 0.1578
-1.750 -0.1972 0.01798 0.00895 -0.0138 1.0000 0.1907
-1.500 -0.1761 0.01759 0.00872 -0.0131 0.9990 0.2375
-1.250 -0.0935 0.01463 0.00856 -0.0235 1.0000 1.0000
-1.000 -0.0609 0.01504 0.00857 -0.0252 0.9960 1.0000
-0.750 -0.0175 0.01549 0.00868 -0.0290 0.9880 1.0000
-0.500 0.0266 0.01597 0.00892 -0.0329 0.9807 1.0000
-0.250 0.0676 0.01632 0.00908 -0.0361 0.9718 1.0000
0.000 0.1073 0.01664 0.00925 -0.0390 0.9628 1.0000
0.250 0.1538 0.01693 0.00939 -0.0431 0.9539 1.0000
0.500 0.2055 0.01703 0.00940 -0.0479 0.9428 1.0000
0.750 0.2505 0.01704 0.00935 -0.0513 0.9305 1.0000
1.000 0.2897 0.01711 0.00938 -0.0536 0.9194 1.0000
1.250 0.3306 0.01718 0.00943 -0.0563 0.9103 1.0000
1.500 0.3774 0.01712 0.00940 -0.0599 0.9024 1.0000
1.750 0.4139 0.01714 0.00944 -0.0616 0.8916 1.0000
2.000 0.4573 0.01703 0.00939 -0.0644 0.8825 1.0000
2.250 0.5057 0.01676 0.00922 -0.0680 0.8744 1.0000
2.500 0.5411 0.01665 0.00918 -0.0691 0.8623 1.0000
2.750 0.5771 0.01648 0.00911 -0.0701 0.8499 1.0000
3.000 0.6153 0.01614 0.00887 -0.0712 0.8357 1.0000
3.250 0.6539 0.01550 0.00834 -0.0716 0.8159 1.0000
3.500 0.6884 0.01486 0.00773 -0.0709 0.7906 1.0000
3.750 0.7153 0.01458 0.00747 -0.0693 0.7639 1.0000
4.000 0.7397 0.01453 0.00746 -0.0676 0.7383 1.0000
4.250 0.7638 0.01452 0.00753 -0.0659 0.7111 1.0000
4.500 0.7871 0.01454 0.00755 -0.0641 0.6806 1.0000
4.750 0.8068 0.01463 0.00766 -0.0616 0.6442 1.0000
5.000 0.8256 0.01471 0.00769 -0.0590 0.5998 1.0000
5.250 0.8431 0.01492 0.00781 -0.0562 0.5485 1.0000
5.500 0.8594 0.01529 0.00800 -0.0534 0.4900 1.0000
5.750 0.8739 0.01590 0.00840 -0.0504 0.4250 1.0000
6.000 0.8849 0.01684 0.00896 -0.0471 0.3493 1.0000
6.250 0.8906 0.01829 0.00980 -0.0431 0.2407 1.0000
6.500 0.8963 0.02023 0.01105 -0.0394 0.1729 1.0000
6.750 0.9107 0.02182 0.01243 -0.0369 0.1487 1.0000
7.000 0.9289 0.02316 0.01369 -0.0352 0.1326 1.0000
7.250 0.9491 0.02451 0.01502 -0.0338 0.1191 1.0000
7.500 0.9647 0.02561 0.01609 -0.0321 0.1010 1.0000
7.750 0.9791 0.02677 0.01740 -0.0300 0.0816 1.0000
8.000 0.9979 0.02968 0.02011 -0.0286 0.0639 1.0000
8.250 1.0147 0.03191 0.02243 -0.0269 0.0516 1.0000
8.500 1.0364 0.03461 0.02555 -0.0253 0.0465 1.0000
8.750 1.0550 0.03750 0.02867 -0.0238 0.0433 1.0000
9.000 1.0687 0.04266 0.03406 -0.0225 0.0407 1.0000
9.250 1.0739 0.04420 0.03618 -0.0189 0.0387 1.0000
9.500 1.0776 0.04708 0.03954 -0.0157 0.0371 1.0000
9.750 1.0767 0.05064 0.04355 -0.0124 0.0366 1.0000
10.000 1.0716 0.05434 0.04763 -0.0090 0.0368 1.0000
10.250 1.0613 0.05809 0.05173 -0.0055 0.0372 1.0000
10.500 1.0465 0.06149 0.05538 -0.0018 0.0376 1.0000
10.750 1.0285 0.06505 0.05917 0.0013 0.0380 1.0000
11.000 1.0098 0.06883 0.06313 0.0034 0.0384 1.0000
11.250 0.9907 0.07300 0.06747 0.0041 0.0388 1.0000
11.500 0.9706 0.07775 0.07236 0.0037 0.0392 1.0000
11.750 0.9512 0.08305 0.07778 0.0021 0.0396 1.0000
12.000 0.9340 0.08900 0.08381 -0.0002 0.0401 1.0000
12.250 0.7715 0.10175 0.09716 -0.0079 0.0500 1.0000
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Polar data table (+)
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