GOE 654 AIRFOIL (goe654-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 654 AIRFOIL (goe654-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.63 at α=7.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe654-il-1000000.txt Download as CSV file: xf-goe654-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 654 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.2181 0.10440 0.10279 -0.0461 0.9902 0.0220
-10.500 -0.2075 0.10046 0.09884 -0.0493 0.9753 0.0227
-10.250 -0.2175 0.08790 0.08627 -0.0611 0.9589 0.0241
-10.000 -0.1749 0.08363 0.08192 -0.0707 0.9396 0.0244
-9.750 -0.1215 0.07813 0.07631 -0.0846 0.9212 0.0247
-9.500 -0.0737 0.07339 0.07135 -0.0967 0.8827 0.0253
-9.250 -0.0661 0.07027 0.06800 -0.0993 0.8347 0.0257
-9.000 -0.0679 0.06710 0.06470 -0.1003 0.8060 0.0265
-8.750 -0.1894 0.04417 0.04145 -0.1161 0.7862 0.0282
-8.500 -0.2367 0.03586 0.03272 -0.1145 0.7703 0.0286
-8.250 -0.2246 0.03420 0.03098 -0.1135 0.7556 0.0288
-8.000 -0.2134 0.03251 0.02915 -0.1124 0.7408 0.0290
-7.750 -0.1979 0.03138 0.02792 -0.1115 0.7257 0.0292
-7.500 -0.1839 0.02995 0.02635 -0.1104 0.7095 0.0295
-7.250 -0.1686 0.02858 0.02481 -0.1093 0.6930 0.0298
-7.000 -0.1528 0.02721 0.02325 -0.1082 0.6745 0.0303
-6.750 -0.1370 0.02563 0.02143 -0.1069 0.6565 0.0312
-6.500 -0.1295 0.02291 0.01798 -0.1043 0.6406 0.0336
-6.250 -0.1184 0.01834 0.01276 -0.1018 0.6254 0.0286
-6.000 -0.0945 0.01789 0.01214 -0.1010 0.6085 0.0284
-5.750 -0.0708 0.01723 0.01131 -0.1002 0.5937 0.0284
-5.500 -0.0467 0.01659 0.01052 -0.0995 0.5814 0.0283
-5.250 -0.0226 0.01582 0.00960 -0.0987 0.5709 0.0283
-5.000 0.0013 0.01466 0.00829 -0.0980 0.5622 0.0284
-4.750 0.0249 0.01346 0.00699 -0.0973 0.5551 0.0288
-4.500 0.0506 0.01287 0.00636 -0.0968 0.5496 0.0292
-4.250 0.0763 0.01243 0.00587 -0.0963 0.5440 0.0294
-4.000 0.1020 0.01206 0.00544 -0.0958 0.5387 0.0296
-3.750 0.1284 0.01171 0.00507 -0.0954 0.5343 0.0299
-3.500 0.1546 0.01139 0.00472 -0.0949 0.5296 0.0302
-3.250 0.1806 0.01113 0.00441 -0.0944 0.5249 0.0305
-3.000 0.2068 0.01087 0.00412 -0.0939 0.5209 0.0307
-2.750 0.2335 0.01061 0.00385 -0.0935 0.5175 0.0311
-2.500 0.2600 0.01039 0.00361 -0.0931 0.5136 0.0314
-2.250 0.2864 0.01021 0.00339 -0.0927 0.5095 0.0319
-2.000 0.3127 0.01011 0.00324 -0.0922 0.5049 0.0325
-1.750 0.3402 0.00996 0.00309 -0.0920 0.5015 0.0329
-1.500 0.3669 0.00975 0.00286 -0.0916 0.4974 0.0335
-1.250 0.3932 0.00955 0.00262 -0.0912 0.4933 0.0342
-1.000 0.4195 0.00946 0.00249 -0.0907 0.4888 0.0351
-0.750 0.4471 0.00935 0.00239 -0.0905 0.4854 0.0360
-0.500 0.4745 0.00926 0.00229 -0.0903 0.4812 0.0371
-0.250 0.5016 0.00921 0.00222 -0.0900 0.4764 0.0382
0.000 0.5283 0.00918 0.00215 -0.0896 0.4712 0.0401
0.250 0.5559 0.00909 0.00209 -0.0894 0.4665 0.0440
0.500 0.5818 0.00886 0.00204 -0.0890 0.4606 0.1095
0.750 0.6038 0.00829 0.00206 -0.0881 0.4549 0.3320
1.000 0.6289 0.00800 0.00210 -0.0876 0.4491 0.4521
1.250 0.6526 0.00778 0.00216 -0.0868 0.4419 0.5656
1.500 0.6751 0.00752 0.00222 -0.0857 0.4347 0.6836
1.750 0.6942 0.00703 0.00235 -0.0835 0.4255 0.9148
2.000 0.7936 0.00727 0.00249 -0.0990 0.4053 0.9988
2.250 0.8227 0.00743 0.00255 -0.0994 0.3913 1.0000
2.500 0.8451 0.00760 0.00263 -0.0982 0.3785 1.0000
2.750 0.8677 0.00776 0.00272 -0.0971 0.3676 1.0000
3.000 0.8899 0.00795 0.00283 -0.0960 0.3575 1.0000
3.250 0.9125 0.00813 0.00295 -0.0949 0.3488 1.0000
3.500 0.9355 0.00829 0.00306 -0.0939 0.3420 1.0000
3.750 0.9587 0.00845 0.00318 -0.0930 0.3360 1.0000
4.000 0.9810 0.00866 0.00333 -0.0919 0.3296 1.0000
4.250 1.0052 0.00878 0.00344 -0.0911 0.3258 1.0000
4.500 1.0286 0.00894 0.00357 -0.0903 0.3214 1.0000
4.750 1.0513 0.00913 0.00372 -0.0893 0.3167 1.0000
5.000 1.0743 0.00931 0.00387 -0.0883 0.3124 1.0000
5.250 1.0985 0.00943 0.00400 -0.0876 0.3087 1.0000
5.500 1.1216 0.00961 0.00414 -0.0868 0.3041 1.0000
5.750 1.1436 0.00984 0.00433 -0.0857 0.2992 1.0000
6.000 1.1673 0.00998 0.00448 -0.0849 0.2960 1.0000
6.250 1.1913 0.01011 0.00462 -0.0842 0.2931 1.0000
6.500 1.2145 0.01028 0.00478 -0.0834 0.2900 1.0000
6.750 1.2367 0.01048 0.00497 -0.0825 0.2861 1.0000
7.000 1.2583 0.01071 0.00518 -0.0814 0.2815 1.0000
7.250 1.2823 0.01083 0.00532 -0.0807 0.2785 1.0000
7.500 1.3049 0.01100 0.00549 -0.0799 0.2747 1.0000
7.750 1.3259 0.01124 0.00570 -0.0787 0.2698 1.0000
8.000 1.3468 0.01146 0.00592 -0.0776 0.2661 1.0000
8.250 1.3694 0.01160 0.00610 -0.0768 0.2630 1.0000
8.500 1.3894 0.01180 0.00630 -0.0754 0.2587 1.0000
8.750 1.4065 0.01207 0.00654 -0.0736 0.2535 1.0000
9.000 1.4258 0.01227 0.00676 -0.0722 0.2496 1.0000
9.250 1.4450 0.01249 0.00699 -0.0708 0.2444 1.0000
9.500 1.4610 0.01284 0.00731 -0.0689 0.2377 1.0000
9.750 1.4801 0.01308 0.00757 -0.0675 0.2320 1.0000
10.000 1.4947 0.01351 0.00794 -0.0656 0.2226 1.0000
10.250 1.5105 0.01391 0.00832 -0.0638 0.2126 1.0000
10.500 1.5233 0.01445 0.00880 -0.0617 0.2005 1.0000
10.750 1.5320 0.01519 0.00946 -0.0591 0.1850 1.0000
11.000 1.5367 0.01616 0.01032 -0.0561 0.1679 1.0000
11.250 1.5376 0.01740 0.01145 -0.0529 0.1472 1.0000
11.500 1.5366 0.01887 0.01280 -0.0499 0.1291 1.0000
11.750 1.5305 0.02082 0.01462 -0.0467 0.1075 1.0000
12.000 1.5202 0.02328 0.01694 -0.0438 0.0836 1.0000
12.250 1.4913 0.02753 0.02101 -0.0405 0.0474 1.0000
12.500 1.4689 0.03176 0.02519 -0.0385 0.0219 1.0000
12.750 1.4690 0.03416 0.02763 -0.0377 0.0186 1.0000
13.000 1.4686 0.03670 0.03023 -0.0371 0.0168 1.0000
13.250 1.4697 0.03916 0.03276 -0.0366 0.0160 1.0000
13.500 1.4715 0.04160 0.03528 -0.0363 0.0156 1.0000
13.750 1.4726 0.04421 0.03797 -0.0361 0.0151 1.0000
14.000 1.4717 0.04706 0.04090 -0.0360 0.0146 1.0000
14.250 1.4700 0.05007 0.04398 -0.0359 0.0143 1.0000
14.500 1.4667 0.05332 0.04732 -0.0360 0.0140 1.0000
14.750 1.4601 0.05701 0.05109 -0.0361 0.0135 1.0000
15.000 1.4521 0.06090 0.05508 -0.0363 0.0132 1.0000
15.250 1.4436 0.06492 0.05920 -0.0366 0.0131 1.0000
15.500 1.4377 0.06867 0.06304 -0.0370 0.0129 1.0000
15.750 1.4329 0.07228 0.06673 -0.0373 0.0127 1.0000
16.000 1.4280 0.07597 0.07050 -0.0378 0.0124 1.0000
16.250 1.4184 0.08036 0.07499 -0.0384 0.0123 1.0000
16.500 1.4102 0.08459 0.07930 -0.0390 0.0121 1.0000
16.750 1.4012 0.08899 0.08379 -0.0398 0.0119 1.0000
17.000 1.3915 0.09357 0.08846 -0.0407 0.0118 1.0000
17.250 1.3823 0.09813 0.09311 -0.0416 0.0117 1.0000
17.500 1.3721 0.10288 0.09794 -0.0427 0.0115 1.0000
17.750 1.3619 0.10769 0.10284 -0.0439 0.0114 1.0000
18.000 1.3516 0.11260 0.10784 -0.0452 0.0113 1.0000
18.250 1.3406 0.11769 0.11302 -0.0468 0.0111 1.0000
18.500 1.3289 0.12296 0.11837 -0.0485 0.0110 1.0000
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