GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL (goe300-il) Reynolds number: 500,000 Max Cl/Cd: 107.59 at α=6° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe300-il-500000.txt Download as CSV file: xf-goe300-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 300 (FRIEDRICHSHAFEN G20) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.2853 0.11128 0.10901 -0.0235 1.0000 0.0223
-9.500 -0.2827 0.10781 0.10556 -0.0271 1.0000 0.0232
-9.250 -0.2824 0.10473 0.10251 -0.0304 1.0000 0.0233
-9.000 -0.2713 0.10109 0.09889 -0.0294 1.0000 0.0236
-8.750 -0.2626 0.09862 0.09645 -0.0295 1.0000 0.0239
-8.500 -0.2562 0.09636 0.09422 -0.0299 1.0000 0.0243
-8.250 -0.2557 0.09448 0.09239 -0.0293 0.9998 0.0247
-8.000 -0.2365 0.09076 0.08866 -0.0340 0.9942 0.0256
-7.750 -0.2177 0.08595 0.08385 -0.0436 0.9808 0.0274
-7.500 -0.1970 0.08025 0.07813 -0.0552 0.9667 0.0276
-7.250 -0.1835 0.07732 0.07519 -0.0535 0.9577 0.0279
-7.000 -0.1698 0.07480 0.07265 -0.0545 0.9442 0.0283
-6.750 -0.1562 0.07227 0.07009 -0.0561 0.9294 0.0288
-6.500 -0.1414 0.06950 0.06726 -0.0585 0.9146 0.0297
-6.250 -0.1069 0.06329 0.06087 -0.0732 0.8984 0.0322
-6.000 -0.0961 0.06000 0.05755 -0.0725 0.8858 0.0326
-5.750 -0.0807 0.05788 0.05537 -0.0722 0.8726 0.0330
-5.500 -0.0610 0.05560 0.05302 -0.0735 0.8588 0.0337
-5.250 -0.0379 0.05289 0.05022 -0.0761 0.8443 0.0350
-5.000 0.0081 0.04646 0.04344 -0.0863 0.8304 0.0376
-4.750 0.0234 0.04377 0.04070 -0.0863 0.8150 0.0382
-4.500 0.0435 0.04253 0.03939 -0.0860 0.7985 0.0391
-4.250 0.0822 0.03909 0.03563 -0.0902 0.7832 0.0435
-4.000 0.1119 0.03492 0.03117 -0.0924 0.7683 0.0437
-3.750 0.1350 0.03175 0.02782 -0.0932 0.7523 0.0433
-3.500 0.1599 0.02935 0.02523 -0.0940 0.7360 0.0449
-3.250 0.1904 0.02342 0.01875 -0.0955 0.7230 0.0447
-3.000 0.2135 0.02643 0.02195 -0.0945 0.7055 0.0491
-2.750 0.2458 0.01831 0.01286 -0.0957 0.6957 0.0514
-2.500 0.2716 0.01934 0.01399 -0.0955 0.6810 0.0527
-2.250 0.2968 0.02103 0.01583 -0.0953 0.6670 0.0564
-2.000 0.3262 0.01784 0.01217 -0.0954 0.6567 0.0574
-1.750 0.3543 0.01503 0.00876 -0.0952 0.6470 0.0607
-1.500 0.3814 0.01533 0.00914 -0.0952 0.6359 0.0625
-1.250 0.4087 0.01532 0.00910 -0.0951 0.6260 0.0648
-1.000 0.4365 0.01422 0.00773 -0.0949 0.6170 0.0662
-0.750 0.4646 0.01351 0.00682 -0.0947 0.6082 0.0683
-0.250 0.5201 0.01242 0.00539 -0.0943 0.5903 0.0707
0.000 0.5473 0.01185 0.00474 -0.0941 0.5811 0.0728
0.250 0.5749 0.01161 0.00445 -0.0939 0.5715 0.0742
0.500 0.6024 0.01140 0.00419 -0.0937 0.5634 0.0756
0.750 0.6299 0.01121 0.00395 -0.0935 0.5546 0.0772
1.000 0.6574 0.01109 0.00378 -0.0933 0.5454 0.0793
1.250 0.6846 0.01100 0.00362 -0.0931 0.5357 0.0810
1.500 0.7122 0.01090 0.00350 -0.0929 0.5269 0.0821
1.750 0.7389 0.01063 0.00318 -0.0926 0.5185 0.0845
2.000 0.7664 0.01051 0.00310 -0.0925 0.5093 0.0871
2.250 0.7935 0.01053 0.00310 -0.0923 0.5001 0.0904
2.500 0.8208 0.01053 0.00309 -0.0921 0.4898 0.0939
2.750 0.8480 0.01051 0.00305 -0.0919 0.4788 0.0968
3.000 0.8748 0.01049 0.00303 -0.0917 0.4664 0.1023
3.250 0.9016 0.01056 0.00307 -0.0914 0.4522 0.1083
3.500 0.9282 0.01061 0.00310 -0.0912 0.4374 0.1166
4.000 0.9813 0.01081 0.00328 -0.0907 0.4099 0.1414
4.250 1.0078 0.01090 0.00340 -0.0905 0.3978 0.1687
4.500 1.0327 0.00964 0.00366 -0.0903 0.3878 1.0000
4.750 1.0585 0.00988 0.00382 -0.0899 0.3781 1.0000
5.000 1.0847 0.01009 0.00399 -0.0896 0.3695 1.0000
5.250 1.1101 0.01037 0.00418 -0.0892 0.3607 1.0000
5.500 1.1363 0.01057 0.00438 -0.0890 0.3530 1.0000
5.750 1.1616 0.01085 0.00461 -0.0886 0.3462 1.0000
6.000 1.1878 0.01104 0.00481 -0.0883 0.3399 1.0000
6.250 1.2130 0.01131 0.00505 -0.0880 0.3325 1.0000
6.500 1.2386 0.01154 0.00529 -0.0876 0.3259 1.0000
6.750 1.2639 0.01178 0.00553 -0.0873 0.3187 1.0000
7.000 1.2890 0.01204 0.00579 -0.0869 0.3112 1.0000
7.250 1.3140 0.01230 0.00605 -0.0865 0.3023 1.0000
7.500 1.3389 0.01255 0.00632 -0.0861 0.2929 1.0000
7.750 1.3630 0.01286 0.00661 -0.0856 0.2810 1.0000
8.000 1.3870 0.01317 0.00690 -0.0851 0.2657 1.0000
8.250 1.4093 0.01361 0.00724 -0.0844 0.2393 1.0000
8.500 1.4281 0.01434 0.00776 -0.0833 0.2033 1.0000
8.750 1.4464 0.01509 0.00837 -0.0821 0.1853 1.0000
9.000 1.4659 0.01571 0.00896 -0.0810 0.1757 1.0000
9.250 1.4841 0.01639 0.00961 -0.0797 0.1683 1.0000
9.500 1.5048 0.01685 0.01011 -0.0788 0.1632 1.0000
9.750 1.5231 0.01746 0.01073 -0.0776 0.1574 1.0000
10.000 1.5403 0.01809 0.01139 -0.0762 0.1518 1.0000
10.250 1.5605 0.01850 0.01188 -0.0752 0.1475 1.0000
10.500 1.5762 0.01909 0.01249 -0.0736 0.1426 1.0000
10.750 1.5897 0.01977 0.01319 -0.0717 0.1376 1.0000
11.000 1.6085 0.02016 0.01367 -0.0705 0.1322 1.0000
11.250 1.6220 0.02087 0.01439 -0.0688 0.1263 1.0000
11.500 1.6383 0.02144 0.01502 -0.0675 0.1203 1.0000
11.750 1.6510 0.02224 0.01582 -0.0658 0.1122 1.0000
12.000 1.6640 0.02306 0.01665 -0.0643 0.1019 1.0000
12.250 1.6707 0.02435 0.01787 -0.0623 0.0875 1.0000
12.500 1.6702 0.02626 0.01966 -0.0599 0.0676 1.0000
12.750 1.6614 0.02896 0.02223 -0.0572 0.0473 1.0000
13.000 1.6538 0.03179 0.02501 -0.0551 0.0358 1.0000
13.250 1.6505 0.03445 0.02771 -0.0536 0.0311 1.0000
13.500 1.6461 0.03736 0.03067 -0.0525 0.0284 1.0000
13.750 1.6439 0.04020 0.03362 -0.0516 0.0266 1.0000
14.000 1.6420 0.04311 0.03665 -0.0510 0.0253 1.0000
14.250 1.6367 0.04650 0.04013 -0.0506 0.0242 1.0000
14.500 1.6279 0.05043 0.04417 -0.0505 0.0233 1.0000
14.750 1.6145 0.05506 0.04891 -0.0506 0.0225 1.0000
15.000 1.6108 0.05861 0.05259 -0.0507 0.0219 1.0000
15.250 1.6047 0.06253 0.05664 -0.0511 0.0213 1.0000
15.500 1.5968 0.06677 0.06100 -0.0516 0.0208 1.0000
15.750 1.5877 0.07128 0.06562 -0.0522 0.0202 1.0000
16.000 1.5775 0.07604 0.07049 -0.0531 0.0198 1.0000
16.250 1.5652 0.08117 0.07573 -0.0541 0.0194 1.0000
16.500 1.5511 0.08670 0.08136 -0.0554 0.0190 1.0000
16.750 1.5354 0.09256 0.08733 -0.0569 0.0187 1.0000
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