GOE 770 AIRFOIL (goe770-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 770 AIRFOIL (goe770-il) Reynolds number: 100,000 Max Cl/Cd: 36.56 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe770-il-100000-n5.txt Download as CSV file: xf-goe770-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 770 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.750 -0.6175 0.08620 0.08028 -0.0574 1.0000 0.0571
-14.500 -0.6962 0.07161 0.06523 -0.0673 1.0000 0.0568
-14.250 -0.7268 0.06505 0.05842 -0.0709 1.0000 0.0570
-14.000 -0.7479 0.06013 0.05326 -0.0731 1.0000 0.0575
-13.750 -0.7644 0.05604 0.04894 -0.0743 1.0000 0.0580
-13.500 -0.7780 0.05251 0.04518 -0.0747 1.0000 0.0586
-13.250 -0.7898 0.04942 0.04183 -0.0745 1.0000 0.0593
-13.000 -0.7950 0.04699 0.03921 -0.0736 1.0000 0.0599
-12.750 -0.7789 0.04545 0.03768 -0.0743 0.9570 0.0607
-12.500 -0.7581 0.04370 0.03577 -0.0758 0.8950 0.0617
-12.000 -0.7387 0.04077 0.03232 -0.0734 0.8210 0.0638
-11.750 -0.7313 0.03934 0.03056 -0.0716 0.7977 0.0652
-11.500 -0.7211 0.03805 0.02900 -0.0700 0.7789 0.0665
-11.250 -0.7051 0.03717 0.02805 -0.0688 0.7631 0.0676
-11.000 -0.6893 0.03625 0.02701 -0.0676 0.7490 0.0689
-10.750 -0.6723 0.03524 0.02585 -0.0665 0.7370 0.0704
-10.500 -0.6547 0.03420 0.02459 -0.0655 0.7266 0.0722
-10.250 -0.6355 0.03327 0.02354 -0.0647 0.7176 0.0740
-10.000 -0.6158 0.03249 0.02274 -0.0639 0.7087 0.0758
-9.500 -0.5759 0.03090 0.02086 -0.0622 0.6933 0.0805
-9.250 -0.5553 0.03013 0.02009 -0.0614 0.6860 0.0826
-9.000 -0.5351 0.02946 0.01935 -0.0605 0.6801 0.0852
-8.750 -0.5140 0.02880 0.01858 -0.0597 0.6737 0.0886
-8.500 -0.4936 0.02810 0.01789 -0.0589 0.6678 0.0915
-8.250 -0.4734 0.02748 0.01723 -0.0580 0.6624 0.0950
-7.750 -0.4329 0.02628 0.01593 -0.0561 0.6520 0.1030
-7.500 -0.4122 0.02574 0.01534 -0.0552 0.6465 0.1080
-7.250 -0.3927 0.02514 0.01474 -0.0542 0.6418 0.1131
-7.000 -0.3721 0.02464 0.01416 -0.0532 0.6377 0.1195
-6.750 -0.3525 0.02408 0.01362 -0.0521 0.6336 0.1264
-6.500 -0.3319 0.02357 0.01314 -0.0512 0.6285 0.1351
-6.250 -0.3117 0.02304 0.01265 -0.0502 0.6237 0.1466
-6.000 -0.2923 0.02243 0.01217 -0.0491 0.6195 0.1642
-5.750 -0.2735 0.02180 0.01177 -0.0479 0.6159 0.2007
-5.500 -0.2530 0.02135 0.01149 -0.0470 0.6121 0.2558
-5.250 -0.2311 0.02101 0.01126 -0.0462 0.6073 0.2951
-5.000 -0.2094 0.02065 0.01103 -0.0453 0.6027 0.3269
-4.750 -0.1876 0.02033 0.01086 -0.0443 0.5986 0.3609
-4.500 -0.1653 0.02014 0.01087 -0.0431 0.5949 0.4022
-4.250 -0.1412 0.02013 0.01092 -0.0423 0.5913 0.4460
-4.000 -0.1173 0.02019 0.01106 -0.0415 0.5863 0.4812
-3.750 -0.0925 0.02027 0.01112 -0.0408 0.5815 0.5079
-3.500 -0.0671 0.02033 0.01112 -0.0401 0.5772 0.5296
-3.250 -0.0409 0.02037 0.01109 -0.0395 0.5733 0.5485
-3.000 -0.0149 0.02045 0.01110 -0.0389 0.5695 0.5653
-2.750 0.0099 0.02055 0.01119 -0.0384 0.5643 0.5815
-2.500 0.0355 0.02063 0.01129 -0.0377 0.5594 0.5964
-2.250 0.0618 0.02067 0.01130 -0.0372 0.5553 0.6103
-2.000 0.0887 0.02070 0.01120 -0.0368 0.5518 0.6237
-1.750 0.1153 0.02075 0.01125 -0.0364 0.5478 0.6329
-1.500 0.1408 0.02085 0.01136 -0.0360 0.5427 0.6415
-1.250 0.1673 0.02089 0.01134 -0.0358 0.5381 0.6499
-1.000 0.1947 0.02089 0.01131 -0.0355 0.5341 0.6578
-0.750 0.2223 0.02089 0.01119 -0.0354 0.5308 0.6682
-0.500 0.2479 0.02101 0.01136 -0.0350 0.5264 0.6774
-0.250 0.2730 0.02114 0.01153 -0.0346 0.5213 0.6866
0.000 0.2995 0.02119 0.01154 -0.0344 0.5168 0.6954
0.250 0.3271 0.02119 0.01151 -0.0341 0.5130 0.7046
0.500 0.3553 0.02118 0.01139 -0.0341 0.5099 0.7153
0.750 0.3788 0.02141 0.01176 -0.0335 0.5042 0.7239
1.000 0.4040 0.02155 0.01193 -0.0331 0.4994 0.7348
1.250 0.4310 0.02160 0.01198 -0.0329 0.4954 0.7455
1.500 0.4590 0.02160 0.01193 -0.0328 0.4921 0.7583
1.750 0.4840 0.02177 0.01216 -0.0323 0.4876 0.7711
2.000 0.5068 0.02201 0.01249 -0.0316 0.4821 0.7862
2.250 0.5327 0.02211 0.01262 -0.0312 0.4777 0.8009
2.500 0.5607 0.02212 0.01262 -0.0311 0.4742 0.8155
2.750 0.5881 0.02223 0.01271 -0.0310 0.4707 0.8320
3.000 0.6101 0.02265 0.01327 -0.0304 0.4651 0.8511
3.250 0.6379 0.02287 0.01355 -0.0305 0.4607 0.8705
3.500 0.6706 0.02298 0.01364 -0.0314 0.4569 0.8906
3.750 0.7080 0.02303 0.01361 -0.0331 0.4539 0.9102
4.000 0.7378 0.02365 0.01437 -0.0344 0.4477 0.9324
4.250 0.7748 0.02398 0.01473 -0.0367 0.4428 0.9518
4.500 0.8149 0.02416 0.01485 -0.0394 0.4392 0.9693
4.750 0.8573 0.02428 0.01487 -0.0424 0.4363 0.9842
5.000 0.8904 0.02504 0.01575 -0.0449 0.4309 1.0000
5.250 0.8999 0.02549 0.01620 -0.0424 0.4270 1.0000
5.500 0.9154 0.02579 0.01646 -0.0407 0.4237 1.0000
5.750 0.9358 0.02596 0.01655 -0.0397 0.4209 1.0000
6.000 0.9571 0.02618 0.01668 -0.0388 0.4182 1.0000
6.250 0.9595 0.02716 0.01779 -0.0356 0.4133 1.0000
6.500 0.9716 0.02780 0.01847 -0.0338 0.4094 1.0000
6.750 0.9899 0.02824 0.01889 -0.0327 0.4064 1.0000
7.000 1.0127 0.02852 0.01912 -0.0322 0.4040 1.0000
7.250 1.0396 0.02871 0.01924 -0.0322 0.4019 1.0000
7.500 1.0351 0.03018 0.02087 -0.0287 0.3978 1.0000
7.750 1.0309 0.03155 0.02233 -0.0253 0.3937 1.0000
8.000 1.0404 0.03242 0.02322 -0.0235 0.3905 1.0000
8.250 1.0621 0.03279 0.02358 -0.0231 0.3879 1.0000
8.500 1.0912 0.03287 0.02361 -0.0233 0.3859 1.0000
8.750 1.0840 0.03482 0.02567 -0.0206 0.3824 1.0000
9.000 1.0099 0.04213 0.03326 -0.0161 0.3739 1.0000
9.250 1.0280 0.04291 0.03404 -0.0158 0.3714 1.0000
9.500 1.0593 0.04255 0.03367 -0.0157 0.3699 1.0000
9.750 1.0958 0.04183 0.03291 -0.0159 0.3687 1.0000
10.250 0.9794 0.05861 0.04999 -0.0143 0.3501 1.0000
10.500 1.0314 0.05549 0.04684 -0.0138 0.3507 1.0000
13.000 0.8657 0.10755 0.09956 -0.0197 0.2727 1.0000
13.250 0.8869 0.10769 0.09973 -0.0194 0.2709 1.0000
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