GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 174 (ALBATROS 5020) AIRFOIL (goe174-il) Reynolds number: 200,000 Max Cl/Cd: 75.29 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe174-il-200000.txt Download as CSV file: xf-goe174-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 174 (ALBATROS 5020) 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 -0.2914 0.08970 0.08654 -0.0240 1.0000 0.0334
-7.000 -0.2962 0.08780 0.08473 -0.0235 1.0000 0.0344
-6.750 -0.3059 0.08650 0.08352 -0.0230 1.0000 0.0352
-6.500 -0.3128 0.08527 0.08235 -0.0259 0.9994 0.0359
-6.250 -0.2697 0.07806 0.07507 -0.0412 0.9932 0.0367
-6.000 -0.2528 0.07403 0.07106 -0.0404 0.9890 0.0376
-5.750 -0.2218 0.07003 0.06702 -0.0452 0.9845 0.0393
-5.500 -0.1857 0.06552 0.06246 -0.0531 0.9765 0.0420
-5.250 -0.1231 0.05773 0.05441 -0.0721 0.9678 0.0464
-5.000 -0.1012 0.05503 0.05178 -0.0721 0.9618 0.0486
-4.750 -0.0610 0.05123 0.04787 -0.0786 0.9535 0.0537
-4.500 -0.0080 0.04518 0.04157 -0.0894 0.9469 0.0592
-4.250 0.0266 0.04246 0.03880 -0.0925 0.9358 0.0638
-4.000 0.0742 0.03784 0.03388 -0.0998 0.9241 0.0730
-3.750 0.1203 0.03450 0.03014 -0.1054 0.9114 0.0858
-3.500 0.1504 0.03232 0.02800 -0.1069 0.8969 0.0900
-3.250 0.1861 0.02977 0.02514 -0.1096 0.8803 0.1027
-3.000 0.2169 0.02802 0.02312 -0.1109 0.8620 0.1169
-2.750 0.2439 0.02668 0.02160 -0.1112 0.8434 0.1320
-2.500 0.2703 0.02541 0.02015 -0.1112 0.8253 0.1469
-1.750 0.3707 0.01717 0.00978 -0.1108 0.7764 0.0706
-1.500 0.3981 0.01592 0.00833 -0.1103 0.7600 0.0679
-1.250 0.4256 0.01498 0.00717 -0.1098 0.7440 0.0659
-1.000 0.4529 0.01430 0.00631 -0.1092 0.7283 0.0649
-0.750 0.4801 0.01377 0.00565 -0.1086 0.7132 0.0646
-0.500 0.5070 0.01338 0.00515 -0.1081 0.6989 0.0655
-0.250 0.5339 0.01313 0.00481 -0.1076 0.6849 0.0680
0.000 0.5608 0.01291 0.00449 -0.1071 0.6713 0.0691
0.250 0.5877 0.01274 0.00422 -0.1067 0.6579 0.0705
0.500 0.6147 0.01262 0.00401 -0.1063 0.6448 0.0746
0.750 0.6417 0.01259 0.00391 -0.1059 0.6315 0.0822
1.000 0.6683 0.01228 0.00397 -0.1057 0.6184 0.2144
1.250 0.6932 0.01071 0.00404 -0.1049 0.6053 1.0000
1.500 0.7198 0.01091 0.00406 -0.1045 0.5916 1.0000
1.750 0.7462 0.01111 0.00410 -0.1040 0.5774 1.0000
2.000 0.7725 0.01130 0.00416 -0.1035 0.5630 1.0000
2.250 0.7986 0.01148 0.00422 -0.1030 0.5475 1.0000
2.500 0.8245 0.01165 0.00428 -0.1025 0.5310 1.0000
2.750 0.8502 0.01182 0.00436 -0.1020 0.5139 1.0000
3.000 0.8759 0.01202 0.00445 -0.1015 0.4971 1.0000
3.250 0.9015 0.01225 0.00456 -0.1010 0.4813 1.0000
3.500 0.9272 0.01251 0.00472 -0.1005 0.4671 1.0000
3.750 0.9529 0.01279 0.00493 -0.1001 0.4543 1.0000
4.000 0.9785 0.01310 0.00515 -0.0997 0.4427 1.0000
4.500 1.0297 0.01371 0.00564 -0.0989 0.4209 1.0000
4.750 1.0555 0.01406 0.00595 -0.0985 0.4122 1.0000
5.000 1.0812 0.01440 0.00626 -0.0982 0.4042 1.0000
5.250 1.1068 0.01474 0.00660 -0.0978 0.3960 1.0000
5.750 1.1565 0.01536 0.00720 -0.0968 0.3763 1.0000
6.000 1.1813 0.01571 0.00755 -0.0964 0.3676 1.0000
6.250 1.2062 0.01605 0.00790 -0.0959 0.3601 1.0000
6.500 1.2310 0.01642 0.00832 -0.0955 0.3530 1.0000
6.750 1.2558 0.01676 0.00872 -0.0950 0.3462 1.0000
7.000 1.2807 0.01720 0.00917 -0.0946 0.3404 1.0000
7.250 1.3048 0.01751 0.00960 -0.0941 0.3331 1.0000
7.500 1.3285 0.01790 0.01002 -0.0935 0.3251 1.0000
7.750 1.3508 0.01816 0.01036 -0.0926 0.3146 1.0000
8.000 1.3729 0.01843 0.01074 -0.0917 0.3035 1.0000
8.250 1.3948 0.01876 0.01114 -0.0908 0.2933 1.0000
8.500 1.4159 0.01909 0.01153 -0.0898 0.2819 1.0000
8.750 1.4364 0.01938 0.01192 -0.0887 0.2680 1.0000
9.000 1.4568 0.01967 0.01234 -0.0876 0.2506 1.0000
9.250 1.4759 0.02008 0.01281 -0.0864 0.2278 1.0000
9.500 1.4887 0.02098 0.01353 -0.0843 0.1786 1.0000
9.750 1.4819 0.02357 0.01549 -0.0799 0.1023 1.0000
10.000 1.4667 0.02649 0.01800 -0.0743 0.0531 1.0000
10.250 1.4612 0.02856 0.02021 -0.0699 0.0444 1.0000
10.500 1.4559 0.03071 0.02250 -0.0663 0.0401 1.0000
10.750 1.4501 0.03310 0.02503 -0.0633 0.0376 1.0000
11.000 1.4506 0.03519 0.02729 -0.0613 0.0353 1.0000
11.250 1.4492 0.03763 0.02985 -0.0597 0.0332 1.0000
11.500 1.4451 0.04051 0.03284 -0.0585 0.0317 1.0000
11.750 1.4349 0.04424 0.03666 -0.0576 0.0306 1.0000
12.000 1.4275 0.04790 0.04044 -0.0570 0.0296 1.0000
12.250 1.4253 0.05112 0.04380 -0.0566 0.0288 1.0000
12.500 1.4219 0.05453 0.04734 -0.0564 0.0280 1.0000
12.750 1.4186 0.05794 0.05084 -0.0561 0.0273 1.0000
13.000 1.4159 0.06125 0.05425 -0.0557 0.0266 1.0000
13.250 1.4140 0.06444 0.05752 -0.0553 0.0260 1.0000
13.500 1.4131 0.06748 0.06063 -0.0548 0.0254 1.0000
13.750 1.4131 0.07036 0.06356 -0.0542 0.0248 1.0000
14.000 1.4149 0.07291 0.06613 -0.0531 0.0241 1.0000
14.250 1.4212 0.07474 0.06798 -0.0505 0.0232 1.0000
14.500 1.4217 0.07790 0.07132 -0.0505 0.0228 1.0000
14.750 1.4230 0.08096 0.07454 -0.0503 0.0223 1.0000
15.000 1.4253 0.08393 0.07768 -0.0497 0.0220 1.0000
15.250 1.4260 0.08723 0.08115 -0.0493 0.0218 1.0000
15.500 1.4245 0.09092 0.08504 -0.0493 0.0216 1.0000
15.750 1.4208 0.09504 0.08935 -0.0497 0.0215 1.0000
16.000 1.4146 0.09963 0.09416 -0.0505 0.0215 1.0000
16.250 1.4060 0.10473 0.09948 -0.0519 0.0215 1.0000
16.500 1.3954 0.11028 0.10525 -0.0539 0.0215 1.0000
16.750 1.3832 0.11626 0.11144 -0.0564 0.0216 1.0000
17.000 1.3695 0.12271 0.11811 -0.0595 0.0218 1.0000
17.250 1.3551 0.12958 0.12518 -0.0632 0.0219 1.0000
17.500 1.3402 0.13680 0.13259 -0.0674 0.0221 1.0000
17.750 1.3246 0.14448 0.14045 -0.0721 0.0223 1.0000
18.000 1.3085 0.15257 0.14871 -0.0773 0.0225 1.0000
18.250 1.2926 0.16097 0.15727 -0.0828 0.0228 1.0000
18.500 1.2771 0.16960 0.16603 -0.0885 0.0231 1.0000
18.750 1.2676 0.17704 0.17357 -0.0931 0.0234 1.0000
19.000 0.8447 0.19822 0.19521 -0.0831 0.0367 1.0000
19.250 0.8472 0.20102 0.19803 -0.0834 0.0382 1.0000
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