GOE 575 AIRFOIL (goe575-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 575 AIRFOIL (goe575-il) Reynolds number: 500,000 Max Cl/Cd: 70.36 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe575-il-500000-n5.txt Download as CSV file: xf-goe575-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 575 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.000 -1.0378 0.04310 0.03922 -0.0953 0.9890 0.0269
-14.750 -1.0379 0.04115 0.03718 -0.0946 0.9878 0.0271
-14.500 -1.0285 0.04010 0.03607 -0.0938 0.9869 0.0274
-14.250 -1.0225 0.03869 0.03454 -0.0928 0.9859 0.0276
-14.000 -1.0265 0.03724 0.03301 -0.0890 0.9828 0.0278
-13.750 -1.0194 0.03646 0.03215 -0.0865 0.9810 0.0281
-13.500 -1.0165 0.03524 0.03081 -0.0837 0.9793 0.0283
-13.250 -1.0064 0.03447 0.02993 -0.0816 0.9781 0.0288
-13.000 -0.9975 0.03347 0.02879 -0.0794 0.9771 0.0291
-12.750 -0.9995 0.03256 0.02775 -0.0744 0.9737 0.0295
-12.500 -0.9955 0.03160 0.02664 -0.0708 0.9712 0.0299
-12.250 -0.9873 0.03071 0.02555 -0.0677 0.9695 0.0304
-12.000 -0.9777 0.02972 0.02438 -0.0650 0.9682 0.0307
-11.750 -0.9719 0.02912 0.02372 -0.0610 0.9659 0.0309
-11.500 -0.9663 0.02874 0.02331 -0.0567 0.9628 0.0312
-11.250 -0.9493 0.02837 0.02291 -0.0548 0.9609 0.0315
-11.000 -0.9289 0.02825 0.02277 -0.0535 0.9596 0.0321
-10.750 -0.9099 0.02772 0.02216 -0.0520 0.9586 0.0324
-10.500 -0.8899 0.02715 0.02149 -0.0507 0.9578 0.0329
-10.250 -0.8881 0.02659 0.02084 -0.0455 0.9538 0.0332
-10.000 -0.8716 0.02604 0.02018 -0.0434 0.9514 0.0337
-9.750 -0.8490 0.02535 0.01936 -0.0425 0.9495 0.0343
-9.500 -0.8238 0.02470 0.01854 -0.0421 0.9482 0.0348
-9.250 -0.7978 0.02392 0.01763 -0.0419 0.9473 0.0352
-9.000 -0.7937 0.02344 0.01713 -0.0369 0.9420 0.0355
-8.750 -0.7728 0.02298 0.01665 -0.0355 0.9399 0.0360
-8.500 -0.7479 0.02246 0.01607 -0.0350 0.9383 0.0363
-8.250 -0.7206 0.02194 0.01551 -0.0348 0.9370 0.0367
-8.000 -0.6926 0.02141 0.01492 -0.0349 0.9360 0.0371
-7.750 -0.6851 0.02105 0.01450 -0.0304 0.9298 0.0376
-7.500 -0.6599 0.02057 0.01395 -0.0298 0.9273 0.0382
-7.250 -0.6321 0.02007 0.01338 -0.0297 0.9256 0.0387
-7.000 -0.6032 0.01953 0.01277 -0.0299 0.9244 0.0391
-6.750 -0.5722 0.01908 0.01223 -0.0304 0.9234 0.0398
-6.500 -0.5643 0.01876 0.01187 -0.0260 0.9165 0.0399
-6.250 -0.5374 0.01818 0.01126 -0.0257 0.9141 0.0404
-6.000 -0.5076 0.01763 0.01071 -0.0260 0.9122 0.0409
-5.750 -0.4765 0.01719 0.01026 -0.0266 0.9107 0.0416
-5.500 -0.4445 0.01674 0.00980 -0.0273 0.9095 0.0423
-5.250 -0.4335 0.01652 0.00956 -0.0235 0.9015 0.0429
-5.000 -0.4042 0.01608 0.00910 -0.0236 0.8984 0.0432
-4.750 -0.3729 0.01563 0.00862 -0.0241 0.8961 0.0441
-4.500 -0.3394 0.01516 0.00812 -0.0251 0.8939 0.0447
-4.250 -0.3264 0.01491 0.00784 -0.0216 0.8820 0.0450
-4.000 -0.2918 0.01444 0.00734 -0.0227 0.8776 0.0456
-3.750 -0.2730 0.01411 0.00702 -0.0206 0.8654 0.0461
-3.500 -0.2356 0.01356 0.00648 -0.0225 0.8599 0.0473
-3.250 -0.2061 0.01322 0.00614 -0.0226 0.8470 0.0484
-3.000 -0.1623 0.01272 0.00562 -0.0259 0.8353 0.0493
-2.750 -0.1002 0.01209 0.00492 -0.0331 0.8146 0.0506
-2.500 -0.0281 0.01152 0.00421 -0.0428 0.7796 0.0524
-2.250 0.0180 0.01130 0.00380 -0.0468 0.7417 0.0545
-2.000 0.0449 0.01131 0.00364 -0.0464 0.7106 0.0556
-1.750 0.0683 0.01132 0.00354 -0.0453 0.6881 0.0573
-1.500 0.0911 0.01133 0.00347 -0.0441 0.6702 0.0588
-1.250 0.1143 0.01131 0.00339 -0.0430 0.6540 0.0613
-1.000 0.1372 0.01126 0.00332 -0.0418 0.6375 0.0664
-0.750 0.1611 0.01114 0.00330 -0.0409 0.6212 0.1010
-0.500 0.1828 0.01115 0.00329 -0.0395 0.6047 0.1161
-0.250 0.2040 0.01118 0.00330 -0.0380 0.5859 0.1286
0.000 0.2251 0.01124 0.00331 -0.0364 0.5687 0.1365
0.250 0.2468 0.01128 0.00333 -0.0350 0.5520 0.1485
0.500 0.2676 0.01136 0.00335 -0.0334 0.5318 0.1558
0.750 0.2887 0.01144 0.00338 -0.0320 0.5121 0.1684
1.250 0.3315 0.01160 0.00348 -0.0291 0.4726 0.1955
1.500 0.3538 0.01168 0.00353 -0.0279 0.4573 0.2066
1.750 0.3765 0.01175 0.00358 -0.0269 0.4419 0.2245
2.000 0.3999 0.01178 0.00365 -0.0260 0.4251 0.2534
2.250 0.4286 0.01156 0.00377 -0.0265 0.4088 0.3899
2.750 0.6926 0.01326 0.00682 -0.0734 0.3569 0.9811
3.250 0.7776 0.01352 0.00693 -0.0801 0.3349 0.9891
3.500 0.8427 0.01340 0.00674 -0.0885 0.3239 0.9973
3.750 0.8814 0.01337 0.00663 -0.0911 0.3114 1.0000
4.000 0.9015 0.01354 0.00675 -0.0895 0.3027 1.0000
4.250 0.9219 0.01369 0.00687 -0.0880 0.2939 1.0000
4.500 0.9421 0.01383 0.00700 -0.0864 0.2879 1.0000
4.750 0.9619 0.01401 0.00713 -0.0848 0.2792 1.0000
5.000 0.9814 0.01420 0.00728 -0.0831 0.2692 1.0000
5.250 1.0014 0.01437 0.00744 -0.0815 0.2632 1.0000
5.500 1.0209 0.01456 0.00760 -0.0799 0.2536 1.0000
5.750 1.0396 0.01480 0.00778 -0.0781 0.2398 1.0000
6.000 1.0582 0.01504 0.00798 -0.0763 0.2294 1.0000
6.250 1.0762 0.01532 0.00819 -0.0744 0.2160 1.0000
6.750 1.1118 0.01590 0.00868 -0.0706 0.1936 1.0000
7.000 1.1286 0.01623 0.00895 -0.0685 0.1841 1.0000
7.250 1.1456 0.01653 0.00924 -0.0665 0.1769 1.0000
7.500 1.1622 0.01686 0.00954 -0.0644 0.1705 1.0000
7.750 1.1791 0.01717 0.00984 -0.0623 0.1640 1.0000
8.000 1.1957 0.01749 0.01015 -0.0603 0.1591 1.0000
8.250 1.2123 0.01781 0.01048 -0.0582 0.1543 1.0000
8.500 1.2290 0.01812 0.01080 -0.0562 0.1495 1.0000
8.750 1.2443 0.01849 0.01118 -0.0540 0.1442 1.0000
9.000 1.2599 0.01885 0.01155 -0.0518 0.1403 1.0000
9.250 1.2759 0.01918 0.01191 -0.0497 0.1359 1.0000
9.500 1.2909 0.01958 0.01231 -0.0475 0.1303 1.0000
9.750 1.3052 0.02001 0.01274 -0.0452 0.1237 1.0000
10.000 1.3181 0.02049 0.01321 -0.0428 0.1151 1.0000
10.250 1.3306 0.02101 0.01372 -0.0403 0.1054 1.0000
10.500 1.3409 0.02167 0.01431 -0.0374 0.0940 1.0000
10.750 1.3498 0.02238 0.01498 -0.0345 0.0848 1.0000
11.000 1.3589 0.02310 0.01569 -0.0316 0.0781 1.0000
11.250 1.3688 0.02378 0.01639 -0.0289 0.0744 1.0000
11.500 1.3772 0.02455 0.01718 -0.0260 0.0710 1.0000
11.750 1.3864 0.02529 0.01795 -0.0234 0.0682 1.0000
12.000 1.3960 0.02601 0.01873 -0.0209 0.0671 1.0000
12.250 1.4035 0.02689 0.01963 -0.0181 0.0645 1.0000
12.500 1.4100 0.02785 0.02063 -0.0154 0.0626 1.0000
12.750 1.4154 0.02889 0.02173 -0.0126 0.0609 1.0000
13.000 1.4242 0.02977 0.02267 -0.0104 0.0597 1.0000
13.250 1.4314 0.03076 0.02373 -0.0081 0.0591 1.0000
13.500 1.4373 0.03189 0.02493 -0.0057 0.0581 1.0000
13.750 1.4431 0.03308 0.02618 -0.0035 0.0571 1.0000
14.000 1.4473 0.03442 0.02760 -0.0013 0.0563 1.0000
14.250 1.4514 0.03583 0.02909 0.0007 0.0562 1.0000
14.500 1.4528 0.03752 0.03084 0.0027 0.0549 1.0000
14.750 1.4511 0.03959 0.03296 0.0047 0.0533 1.0000
15.000 1.4514 0.04158 0.03504 0.0063 0.0528 1.0000
15.250 1.4548 0.04340 0.03695 0.0075 0.0521 1.0000
15.500 1.4565 0.04544 0.03910 0.0086 0.0519 1.0000
15.750 1.4574 0.04763 0.04138 0.0096 0.0515 1.0000
16.000 1.4597 0.04974 0.04359 0.0104 0.0505 1.0000
16.250 1.4582 0.05230 0.04625 0.0110 0.0500 1.0000
16.500 1.4563 0.05500 0.04905 0.0115 0.0499 1.0000
16.750 1.4527 0.05798 0.05211 0.0119 0.0485 1.0000
17.000 1.4478 0.06119 0.05541 0.0120 0.0480 1.0000
17.250 1.4425 0.06452 0.05883 0.0120 0.0472 1.0000
17.500 1.4335 0.06837 0.06277 0.0117 0.0464 1.0000
17.750 1.4272 0.07200 0.06651 0.0114 0.0465 1.0000
18.000 1.4174 0.07614 0.07073 0.0107 0.0453 1.0000
18.250 1.4093 0.08011 0.07481 0.0101 0.0451 1.0000
18.500 1.4037 0.08381 0.07862 0.0094 0.0445 1.0000
18.750 1.3975 0.08762 0.08255 0.0086 0.0440 1.0000
19.000 1.3917 0.09144 0.08646 0.0078 0.0427 1.0000
19.250 1.3826 0.09572 0.09086 0.0067 0.0429 1.0000
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Polar data table (+)
Polar graphs
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