GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 173 (ALBATROS 6020) AIRFOIL (goe173-il) Reynolds number: 200,000 Max Cl/Cd: 77.7 at α=3° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe173-il-200000.txt Download as CSV file: xf-goe173-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 173 (ALBATROS 6020) 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
------ -------- --------- --------- -------- -------- --------
-7.250 -0.2735 0.09369 0.09060 -0.0237 1.0000 0.0262
-7.000 -0.2781 0.09238 0.08938 -0.0238 1.0000 0.0265
-6.750 -0.2845 0.09129 0.08839 -0.0239 1.0000 0.0267
-6.500 -0.2706 0.08888 0.08601 -0.0305 0.9965 0.0269
-6.250 -0.2244 0.08363 0.08069 -0.0443 0.9891 0.0271
-6.000 -0.1998 0.07695 0.07402 -0.0491 0.9844 0.0275
-5.750 -0.1810 0.07242 0.06951 -0.0496 0.9778 0.0283
-5.500 -0.1483 0.06811 0.06517 -0.0553 0.9721 0.0298
-5.250 -0.1106 0.06377 0.06076 -0.0632 0.9624 0.0323
-5.000 -0.0421 0.05910 0.05585 -0.0799 0.9537 0.0355
-4.750 0.0051 0.05322 0.04979 -0.0896 0.9454 0.0362
-4.500 0.0248 0.04889 0.04550 -0.0908 0.9344 0.0376
-4.250 0.0574 0.04554 0.04208 -0.0944 0.9223 0.0398
-4.000 0.0989 0.04192 0.03826 -0.1000 0.9091 0.0440
-3.750 0.1436 0.03751 0.03353 -0.1062 0.8951 0.0492
-3.500 0.1719 0.03529 0.03122 -0.1077 0.8794 0.0544
-3.250 0.2121 0.03197 0.02745 -0.1113 0.8640 0.0620
-3.000 0.2369 0.03012 0.02551 -0.1118 0.8480 0.0670
-2.750 0.2691 0.02781 0.02282 -0.1132 0.8329 0.0771
-2.500 0.2979 0.02624 0.02093 -0.1138 0.8177 0.0907
-2.250 0.3252 0.02484 0.01928 -0.1141 0.8031 0.1052
-2.000 0.3519 0.02345 0.01770 -0.1143 0.7894 0.1202
-1.750 0.3783 0.02211 0.01621 -0.1144 0.7769 0.1363
-1.500 0.4050 0.02116 0.01507 -0.1145 0.7650 0.1641
-1.000 0.4761 0.01635 0.00885 -0.1132 0.7442 0.0708
-0.750 0.5042 0.01540 0.00767 -0.1128 0.7329 0.0693
-0.500 0.5320 0.01470 0.00675 -0.1123 0.7222 0.0688
-0.250 0.5595 0.01407 0.00595 -0.1118 0.7116 0.0674
0.000 0.5865 0.01357 0.00537 -0.1113 0.6996 0.0674
0.250 0.6133 0.01318 0.00494 -0.1108 0.6874 0.0684
0.500 0.6402 0.01292 0.00464 -0.1104 0.6754 0.0714
0.750 0.6670 0.01270 0.00437 -0.1099 0.6633 0.0749
1.000 0.6940 0.01249 0.00411 -0.1096 0.6510 0.0791
1.250 0.7209 0.01239 0.00394 -0.1091 0.6378 0.0877
1.500 0.7422 0.01045 0.00395 -0.1077 0.6245 1.0000
1.750 0.7686 0.01056 0.00385 -0.1071 0.6087 1.0000
2.000 0.7947 0.01068 0.00382 -0.1066 0.5907 1.0000
2.250 0.8204 0.01083 0.00381 -0.1060 0.5708 1.0000
2.500 0.8457 0.01101 0.00384 -0.1053 0.5487 1.0000
2.750 0.8706 0.01124 0.00389 -0.1046 0.5235 1.0000
3.000 0.8951 0.01152 0.00399 -0.1039 0.4950 1.0000
3.250 0.9193 0.01185 0.00413 -0.1032 0.4660 1.0000
3.500 0.9437 0.01222 0.00434 -0.1026 0.4402 1.0000
3.750 0.9680 0.01263 0.00457 -0.1020 0.4204 1.0000
4.000 0.9928 0.01303 0.00485 -0.1014 0.4047 1.0000
4.250 1.0175 0.01346 0.00514 -0.1010 0.3926 1.0000
4.500 1.0428 0.01386 0.00550 -0.1006 0.3819 1.0000
4.750 1.0681 0.01427 0.00586 -0.1002 0.3731 1.0000
5.000 1.0933 0.01474 0.00624 -0.0998 0.3658 1.0000
5.250 1.1190 0.01514 0.00666 -0.0995 0.3593 1.0000
5.500 1.1447 0.01558 0.00710 -0.0993 0.3536 1.0000
5.750 1.1705 0.01610 0.00758 -0.0991 0.3489 1.0000
6.000 1.1963 0.01650 0.00807 -0.0988 0.3441 1.0000
6.250 1.2216 0.01694 0.00851 -0.0985 0.3381 1.0000
6.500 1.2460 0.01735 0.00900 -0.0980 0.3305 1.0000
6.750 1.2703 0.01776 0.00940 -0.0976 0.3228 1.0000
7.000 1.2930 0.01803 0.00977 -0.0968 0.3122 1.0000
7.250 1.3159 0.01838 0.01016 -0.0962 0.3030 1.0000
7.500 1.3382 0.01869 0.01050 -0.0954 0.2929 1.0000
7.750 1.3596 0.01883 0.01081 -0.0944 0.2811 1.0000
8.000 1.3815 0.01906 0.01116 -0.0935 0.2701 1.0000
8.250 1.4018 0.01920 0.01138 -0.0924 0.2522 1.0000
8.500 1.4223 0.01941 0.01166 -0.0913 0.2274 1.0000
8.750 1.4384 0.02014 0.01216 -0.0896 0.1661 1.0000
9.000 1.4281 0.02355 0.01460 -0.0851 0.0486 1.0000
9.250 1.4351 0.02521 0.01618 -0.0823 0.0311 1.0000
9.500 1.4444 0.02651 0.01759 -0.0797 0.0275 1.0000
9.750 1.4515 0.02773 0.01900 -0.0768 0.0258 1.0000
10.000 1.4557 0.02919 0.02062 -0.0739 0.0242 1.0000
10.250 1.4565 0.03093 0.02253 -0.0709 0.0229 1.0000
10.500 1.4541 0.03303 0.02480 -0.0681 0.0222 1.0000
10.750 1.4493 0.03555 0.02749 -0.0658 0.0217 1.0000
11.000 1.4426 0.03852 0.03065 -0.0640 0.0213 1.0000
11.250 1.4349 0.04190 0.03419 -0.0628 0.0211 1.0000
11.500 1.4264 0.04557 0.03801 -0.0619 0.0208 1.0000
11.750 1.4181 0.04936 0.04192 -0.0612 0.0207 1.0000
12.000 1.4128 0.05287 0.04552 -0.0605 0.0205 1.0000
12.250 1.4097 0.05614 0.04891 -0.0598 0.0205 1.0000
12.500 1.4081 0.05922 0.05209 -0.0589 0.0204 1.0000
12.750 1.4084 0.06202 0.05498 -0.0578 0.0203 1.0000
13.000 1.4113 0.06457 0.05762 -0.0564 0.0202 1.0000
13.250 1.4144 0.06718 0.06036 -0.0554 0.0200 1.0000
13.500 1.4169 0.06994 0.06325 -0.0546 0.0196 1.0000
13.750 1.4190 0.07283 0.06631 -0.0539 0.0192 1.0000
14.000 1.4227 0.07559 0.06922 -0.0528 0.0191 1.0000
14.250 1.4258 0.07858 0.07239 -0.0516 0.0192 1.0000
14.500 1.4269 0.08199 0.07599 -0.0508 0.0194 1.0000
14.750 1.4256 0.08589 0.08010 -0.0503 0.0197 1.0000
15.000 1.4218 0.09028 0.08470 -0.0500 0.0200 1.0000
15.250 1.4300 0.09407 0.08866 -0.0481 0.0208 1.0000
15.500 1.4232 0.09802 0.09279 -0.0496 0.0211 1.0000
15.750 1.4126 0.10285 0.09784 -0.0518 0.0214 1.0000
16.000 1.3965 0.10914 0.10444 -0.0551 0.0221 1.0000
16.250 1.3732 0.11737 0.11303 -0.0596 0.0230 1.0000
16.500 1.3507 0.12594 0.12188 -0.0647 0.0235 1.0000
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Polar data table (+)
Polar graphs
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