GOE 100 (SOPWITH) AIRFOIL (goe100-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 100 (SOPWITH) AIRFOIL (goe100-il) Reynolds number: 100,000 Max Cl/Cd: 50.92 at α=2.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe100-il-100000-n5.txt Download as CSV file: xf-goe100-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 100 (SOPWITH) 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
------ -------- --------- --------- -------- -------- --------
-7.500 -0.3786 0.09488 0.09031 -0.0218 1.0000 0.0377
-7.250 -0.3814 0.09234 0.08786 -0.0217 1.0000 0.0380
-7.000 -0.3815 0.08950 0.08509 -0.0224 1.0000 0.0383
-6.750 -0.3805 0.08655 0.08220 -0.0234 1.0000 0.0385
-6.500 -0.3788 0.08353 0.07924 -0.0244 1.0000 0.0385
-6.250 -0.3764 0.08045 0.07620 -0.0253 1.0000 0.0382
-6.000 -0.3731 0.07725 0.07303 -0.0263 1.0000 0.0376
-5.500 -0.3597 0.06871 0.06442 -0.0295 1.0000 0.0233
-5.250 -0.3517 0.06538 0.06107 -0.0299 1.0000 0.0222
-5.000 -0.3403 0.06174 0.05738 -0.0311 1.0000 0.0213
-4.750 -0.3256 0.05789 0.05344 -0.0326 1.0000 0.0208
-4.500 -0.3078 0.05391 0.04934 -0.0344 1.0000 0.0208
-4.250 -0.2825 0.04943 0.04467 -0.0373 0.9991 0.0212
-4.000 -0.2447 0.04405 0.03898 -0.0422 0.9960 0.0213
-3.750 -0.2069 0.03865 0.03316 -0.0463 0.9930 0.0208
-3.500 -0.1688 0.03311 0.02708 -0.0495 0.9904 0.0204
-3.250 -0.1302 0.02804 0.02125 -0.0519 0.9885 0.0203
-3.000 -0.0923 0.02412 0.01649 -0.0536 0.9871 0.0209
-2.750 -0.0572 0.02160 0.01329 -0.0546 0.9846 0.0236
-2.500 -0.0217 0.02011 0.01152 -0.0560 0.9814 0.0274
-2.250 0.0176 0.01885 0.00996 -0.0579 0.9779 0.0347
-2.000 0.0539 0.01786 0.00886 -0.0595 0.9717 0.0579
-1.750 0.0917 0.01752 0.00856 -0.0619 0.9660 0.0986
-1.500 0.1256 0.01709 0.00801 -0.0631 0.9596 0.1114
-1.250 0.1637 0.01673 0.00759 -0.0652 0.9554 0.1303
-1.000 0.1952 0.01639 0.00724 -0.0659 0.9473 0.1585
-0.750 0.2365 0.01594 0.00675 -0.0685 0.9397 0.2001
-0.500 0.2765 0.01541 0.00632 -0.0708 0.9297 0.2544
0.250 0.3869 0.01306 0.00543 -0.0748 0.9005 1.0000
0.500 0.4194 0.01295 0.00518 -0.0754 0.8868 1.0000
0.750 0.4507 0.01284 0.00495 -0.0756 0.8711 1.0000
1.000 0.4793 0.01277 0.00479 -0.0753 0.8523 1.0000
1.250 0.5091 0.01268 0.00462 -0.0752 0.8325 1.0000
1.500 0.5362 0.01265 0.00453 -0.0746 0.8093 1.0000
1.750 0.5633 0.01263 0.00444 -0.0739 0.7831 1.0000
2.000 0.5900 0.01263 0.00437 -0.0732 0.7503 1.0000
2.250 0.6168 0.01266 0.00430 -0.0725 0.7062 1.0000
2.500 0.6436 0.01278 0.00418 -0.0716 0.6468 1.0000
2.750 0.6681 0.01312 0.00416 -0.0705 0.5793 1.0000
3.000 0.6909 0.01361 0.00433 -0.0693 0.5212 1.0000
3.250 0.7135 0.01413 0.00464 -0.0682 0.4714 1.0000
3.500 0.7363 0.01463 0.00496 -0.0673 0.4267 1.0000
3.750 0.7593 0.01514 0.00532 -0.0664 0.3883 1.0000
4.000 0.7804 0.01582 0.00574 -0.0653 0.3339 1.0000
4.250 0.8019 0.01649 0.00614 -0.0644 0.2867 1.0000
4.500 0.8229 0.01727 0.00652 -0.0636 0.2241 1.0000
4.750 0.8447 0.01802 0.00695 -0.0628 0.1747 1.0000
5.000 0.8670 0.01876 0.00746 -0.0620 0.1318 1.0000
5.250 0.8840 0.02043 0.00851 -0.0606 0.0254 1.0000
5.500 0.9059 0.02139 0.00961 -0.0594 0.0204 1.0000
5.750 0.9285 0.02226 0.01073 -0.0583 0.0188 1.0000
6.000 0.9508 0.02317 0.01189 -0.0572 0.0181 1.0000
6.250 0.9724 0.02420 0.01318 -0.0561 0.0167 1.0000
6.500 0.9928 0.02538 0.01463 -0.0548 0.0154 1.0000
6.750 1.0119 0.02664 0.01622 -0.0534 0.0150 1.0000
7.000 1.0292 0.02799 0.01782 -0.0517 0.0147 1.0000
7.250 1.0445 0.02942 0.01946 -0.0498 0.0146 1.0000
7.500 1.0583 0.03093 0.02114 -0.0477 0.0146 1.0000
7.750 1.0715 0.03252 0.02285 -0.0455 0.0147 1.0000
8.000 1.0852 0.03425 0.02467 -0.0434 0.0144 1.0000
8.250 1.1003 0.03618 0.02666 -0.0416 0.0139 1.0000
8.500 1.1176 0.03842 0.02894 -0.0402 0.0131 1.0000
8.750 1.1372 0.04081 0.03142 -0.0391 0.0128 1.0000
9.000 1.1554 0.04291 0.03379 -0.0376 0.0133 1.0000
9.250 1.1713 0.04520 0.03640 -0.0358 0.0139 1.0000
9.500 1.1846 0.04777 0.03942 -0.0338 0.0147 1.0000
9.750 1.1949 0.05066 0.04263 -0.0317 0.0155 1.0000
10.000 1.2018 0.05387 0.04615 -0.0296 0.0163 1.0000
10.250 1.2052 0.05755 0.05011 -0.0274 0.0172 1.0000
10.500 1.2197 0.05887 0.05180 -0.0249 0.0210 1.0000
10.750 1.2089 0.06149 0.05482 -0.0210 0.0223 1.0000
11.000 1.1997 0.06484 0.05847 -0.0183 0.0235 1.0000
11.250 1.1909 0.06870 0.06255 -0.0165 0.0244 1.0000
12.750 0.9143 0.09118 0.08612 -0.0109 0.0171 1.0000
13.000 0.8862 0.09655 0.09165 -0.0139 0.0169 1.0000
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Polar data table (+)
Polar graphs
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