GOE 54 AIRFOIL (goe54-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: GOE 54 AIRFOIL (goe54-il) Reynolds number: 200,000 Max Cl/Cd: 64.23 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe54-il-200000-n5.txt Download as CSV file: xf-goe54-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 54 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.5327 0.10548 0.10213 0.0370 1.0000 0.0234
-8.000 -0.5267 0.10210 0.09878 0.0349 1.0000 0.0239
-7.750 -0.5207 0.09874 0.09545 0.0321 1.0000 0.0244
-7.500 -0.5126 0.09519 0.09192 0.0276 1.0000 0.0246
-7.250 -0.4962 0.09084 0.08756 0.0177 1.0000 0.0248
-7.000 -0.4789 0.08618 0.08288 0.0111 1.0000 0.0249
-6.750 -0.4707 0.08238 0.07911 0.0129 1.0000 0.0251
-6.500 -0.4579 0.07870 0.07545 0.0117 1.0000 0.0254
-6.250 -0.4418 0.07499 0.07174 0.0089 1.0000 0.0258
-6.000 -0.4229 0.07121 0.06794 0.0053 1.0000 0.0263
-5.750 -0.4013 0.06735 0.06405 0.0013 1.0000 0.0271
-5.500 -0.3747 0.06342 0.06004 -0.0036 1.0000 0.0286
-5.250 -0.3304 0.05913 0.05540 -0.0124 1.0000 0.0295
-5.000 -0.3005 0.05540 0.05146 -0.0158 1.0000 0.0296
-4.750 -0.2848 0.05135 0.04751 -0.0163 1.0000 0.0299
-4.500 -0.2636 0.04884 0.04424 -0.0168 0.6746 0.0303
-4.250 -0.2416 0.04639 0.04144 -0.0177 0.5982 0.0310
-4.000 -0.2156 0.04399 0.03869 -0.0191 0.5512 0.0325
-3.500 -0.1450 0.04022 0.03387 -0.0220 0.5050 0.0352
-3.250 -0.1180 0.03734 0.03074 -0.0229 0.4899 0.0355
-3.000 -0.0944 0.03438 0.02774 -0.0238 0.4765 0.0360
-2.750 -0.0687 0.03233 0.02557 -0.0246 0.4646 0.0370
-2.500 -0.0403 0.03068 0.02370 -0.0251 0.4537 0.0390
-2.250 -0.0058 0.03028 0.02275 -0.0249 0.4430 0.0416
-2.000 0.0243 0.02878 0.02089 -0.0251 0.4328 0.0420
-1.750 0.0505 0.02625 0.01835 -0.0259 0.4229 0.0427
-1.500 0.0785 0.02475 0.01674 -0.0262 0.4126 0.0439
-1.250 0.1075 0.02365 0.01542 -0.0264 0.4032 0.0459
-1.000 0.1379 0.02282 0.01426 -0.0262 0.3934 0.0496
-0.750 0.1660 0.02162 0.01299 -0.0265 0.3833 0.0522
-0.500 0.1960 0.02110 0.01213 -0.0263 0.3732 0.0567
-0.250 0.2242 0.01994 0.01092 -0.0265 0.3619 0.0589
0.250 0.2818 0.01868 0.00935 -0.0263 0.3385 0.0706
0.500 0.3125 0.01817 0.00853 -0.0254 0.3268 0.0478
0.750 0.3412 0.01733 0.00761 -0.0252 0.3146 0.0443
1.000 0.3697 0.01690 0.00707 -0.0250 0.3032 0.0455
1.250 0.3984 0.01658 0.00656 -0.0246 0.2934 0.0429
1.500 0.4268 0.01636 0.00621 -0.0243 0.2840 0.0412
1.750 0.4549 0.01596 0.00578 -0.0242 0.2755 0.0407
2.000 0.4829 0.01569 0.00546 -0.0240 0.2671 0.0405
2.250 0.5110 0.01547 0.00522 -0.0238 0.2604 0.0405
2.500 0.5390 0.01531 0.00505 -0.0237 0.2545 0.0407
2.750 0.5669 0.01529 0.00497 -0.0235 0.2497 0.0421
3.000 0.5949 0.01507 0.00484 -0.0235 0.2455 0.0441
3.250 0.6231 0.01500 0.00482 -0.0234 0.2411 0.0445
3.500 0.6511 0.01501 0.00482 -0.0234 0.2368 0.0451
3.750 0.6789 0.01511 0.00486 -0.0233 0.2326 0.0459
4.000 0.7069 0.01520 0.00495 -0.0232 0.2285 0.0470
4.250 0.7348 0.01531 0.00507 -0.0230 0.2239 0.0488
4.500 0.7626 0.01544 0.00518 -0.0229 0.2195 0.0534
4.750 0.7899 0.01569 0.00536 -0.0227 0.2155 0.0558
5.000 0.8176 0.01585 0.00557 -0.0226 0.2117 0.0600
5.250 0.8455 0.01588 0.00588 -0.0225 0.2075 0.2290
5.750 0.8954 0.01500 0.00641 -0.0213 0.1996 1.0000
6.000 0.9227 0.01530 0.00676 -0.0211 0.1956 1.0000
6.250 0.9501 0.01559 0.00710 -0.0210 0.1911 1.0000
6.500 0.9771 0.01590 0.00743 -0.0208 0.1869 1.0000
6.750 1.0038 0.01630 0.00780 -0.0207 0.1832 1.0000
7.000 1.0310 0.01658 0.00822 -0.0205 0.1780 1.0000
7.250 1.0579 0.01683 0.00851 -0.0204 0.1720 1.0000
7.500 1.0846 0.01714 0.00886 -0.0203 0.1664 1.0000
7.750 1.1113 0.01746 0.00929 -0.0201 0.1611 1.0000
8.000 1.1377 0.01780 0.00964 -0.0200 0.1564 1.0000
8.250 1.1641 0.01816 0.01011 -0.0198 0.1507 1.0000
8.500 1.1902 0.01853 0.01055 -0.0197 0.1452 1.0000
8.750 1.2159 0.01898 0.01105 -0.0195 0.1410 1.0000
9.000 1.2416 0.01943 0.01164 -0.0193 0.1364 1.0000
9.250 1.2669 0.01992 0.01220 -0.0191 0.1314 1.0000
9.500 1.2919 0.02046 0.01284 -0.0189 0.1267 1.0000
9.750 1.3167 0.02101 0.01352 -0.0188 0.1208 1.0000
10.000 1.3405 0.02169 0.01424 -0.0186 0.1148 1.0000
10.250 1.3650 0.02228 0.01504 -0.0184 0.1084 1.0000
10.500 1.3879 0.02308 0.01590 -0.0182 0.1008 1.0000
10.750 1.4111 0.02383 0.01679 -0.0180 0.0895 1.0000
11.000 1.4329 0.02479 0.01782 -0.0178 0.0745 1.0000
11.250 1.4518 0.02619 0.01919 -0.0177 0.0641 1.0000
11.500 1.4687 0.02784 0.02089 -0.0175 0.0578 1.0000
11.750 1.4858 0.02932 0.02253 -0.0172 0.0536 1.0000
12.000 1.4994 0.03121 0.02456 -0.0169 0.0501 1.0000
12.250 1.5113 0.03319 0.02670 -0.0167 0.0473 1.0000
12.500 1.5225 0.03510 0.02883 -0.0165 0.0448 1.0000
12.750 1.5279 0.03763 0.03154 -0.0166 0.0426 1.0000
13.000 1.5232 0.04117 0.03527 -0.0174 0.0411 1.0000
13.250 1.5057 0.04863 0.04300 -0.0244 0.0408 1.0000
13.500 1.4837 0.05715 0.05172 -0.0310 0.0406 1.0000
13.750 1.4584 0.06510 0.05982 -0.0357 0.0406 1.0000
14.000 1.4328 0.07280 0.06765 -0.0398 0.0406 1.0000
14.250 1.4082 0.08029 0.07525 -0.0434 0.0405 1.0000
14.500 1.3858 0.08744 0.08249 -0.0468 0.0402 1.0000
14.750 1.3661 0.09417 0.08927 -0.0499 0.0397 1.0000
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Polar data table (+)
Polar graphs
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