GIII BL207 AIRFOIL (giiih-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GIII BL207 AIRFOIL (giiih-il) Reynolds number: 100,000 Max Cl/Cd: 44.5 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiih-il-100000-n5.txt Download as CSV file: xf-giiih-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL207 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
------ -------- --------- --------- -------- -------- --------
-10.000 -0.5714 0.11431 0.10933 -0.0008 1.0000 0.0432
-9.750 -0.5739 0.11018 0.10527 -0.0058 1.0000 0.0439
-9.500 -0.5745 0.10573 0.10085 -0.0099 1.0000 0.0442
-9.250 -0.5756 0.10091 0.09608 -0.0144 1.0000 0.0443
-8.750 -0.4738 0.07704 0.07242 -0.0227 1.0000 0.0309
-8.500 -0.5766 0.08342 0.07859 -0.0221 1.0000 0.0315
-8.250 -0.5763 0.07918 0.07436 -0.0226 1.0000 0.0308
-8.000 -0.5761 0.07478 0.06993 -0.0239 1.0000 0.0300
-7.750 -0.5751 0.07024 0.06533 -0.0254 1.0000 0.0292
-7.500 -0.5726 0.06561 0.06060 -0.0266 1.0000 0.0284
-7.250 -0.5683 0.06095 0.05579 -0.0274 1.0000 0.0278
-7.000 -0.5621 0.05635 0.05095 -0.0277 1.0000 0.0272
-6.750 -0.5541 0.05188 0.04623 -0.0274 1.0000 0.0269
-6.500 -0.5445 0.04759 0.04165 -0.0266 1.0000 0.0267
-6.250 -0.5334 0.04362 0.03735 -0.0254 1.0000 0.0268
-6.000 -0.5204 0.04028 0.03366 -0.0239 1.0000 0.0285
-5.750 -0.5064 0.03705 0.02998 -0.0220 1.0000 0.0300
-5.500 -0.4919 0.03396 0.02646 -0.0200 1.0000 0.0304
-5.250 -0.4759 0.03116 0.02321 -0.0180 1.0000 0.0308
-5.000 -0.4583 0.02877 0.02036 -0.0161 1.0000 0.0314
-4.750 -0.4395 0.02683 0.01800 -0.0143 1.0000 0.0321
-4.500 -0.4219 0.02486 0.01593 -0.0132 1.0000 0.0347
-4.250 -0.4027 0.02379 0.01468 -0.0119 1.0000 0.0376
-4.000 -0.3816 0.02234 0.01298 -0.0105 1.0000 0.0394
-3.750 -0.3601 0.02104 0.01146 -0.0092 1.0000 0.0414
-3.500 -0.3280 0.01982 0.01000 -0.0100 0.9962 0.0442
-3.250 -0.2951 0.01864 0.00888 -0.0116 0.9908 0.0511
-3.000 -0.2605 0.01776 0.00784 -0.0131 0.9856 0.0577
-2.750 -0.2286 0.01690 0.00703 -0.0144 0.9790 0.0681
-2.500 -0.1955 0.01618 0.00628 -0.0158 0.9729 0.0782
-2.250 -0.1617 0.01561 0.00570 -0.0173 0.9666 0.0961
-2.000 -0.1295 0.01487 0.00520 -0.0186 0.9601 0.1507
-1.750 -0.1127 0.01251 0.00524 -0.0164 0.9543 0.7371
-1.500 -0.0843 0.01251 0.00548 -0.0147 0.9491 0.8584
-1.250 -0.0412 0.01275 0.00569 -0.0160 0.9469 0.9307
-1.000 0.0327 0.01295 0.00569 -0.0243 0.9532 0.9767
-0.750 0.0768 0.01287 0.00548 -0.0281 0.9468 0.9830
-0.500 0.1181 0.01279 0.00529 -0.0313 0.9395 0.9879
-0.250 0.1582 0.01272 0.00515 -0.0343 0.9313 0.9931
0.000 0.1992 0.01263 0.00500 -0.0374 0.9238 0.9978
0.250 0.2311 0.01258 0.00492 -0.0386 0.9122 1.0000
0.500 0.2586 0.01252 0.00482 -0.0386 0.8976 1.0000
0.750 0.2844 0.01246 0.00473 -0.0382 0.8823 1.0000
1.000 0.3086 0.01243 0.00469 -0.0374 0.8677 1.0000
1.250 0.3320 0.01244 0.00471 -0.0366 0.8543 1.0000
1.500 0.3550 0.01247 0.00474 -0.0357 0.8410 1.0000
1.750 0.3780 0.01250 0.00479 -0.0347 0.8275 1.0000
2.000 0.4009 0.01255 0.00486 -0.0336 0.8138 1.0000
2.250 0.4238 0.01260 0.00497 -0.0325 0.7998 1.0000
2.500 0.4468 0.01266 0.00507 -0.0314 0.7854 1.0000
2.750 0.4698 0.01273 0.00519 -0.0303 0.7703 1.0000
3.000 0.4930 0.01279 0.00531 -0.0291 0.7542 1.0000
3.250 0.5154 0.01286 0.00549 -0.0278 0.7338 1.0000
3.500 0.5366 0.01284 0.00545 -0.0259 0.6994 1.0000
3.750 0.5566 0.01286 0.00538 -0.0236 0.6479 1.0000
4.000 0.5771 0.01302 0.00539 -0.0216 0.5882 1.0000
4.250 0.5963 0.01340 0.00548 -0.0195 0.4990 1.0000
4.500 0.6128 0.01420 0.00572 -0.0174 0.3909 1.0000
4.750 0.6295 0.01520 0.00622 -0.0157 0.2849 1.0000
5.000 0.6444 0.01661 0.00690 -0.0141 0.1543 1.0000
5.250 0.6624 0.01781 0.00775 -0.0128 0.0997 1.0000
5.500 0.6819 0.01884 0.00867 -0.0116 0.0772 1.0000
5.750 0.7019 0.01980 0.00968 -0.0104 0.0640 1.0000
6.000 0.7215 0.02083 0.01076 -0.0092 0.0566 1.0000
6.250 0.7412 0.02192 0.01196 -0.0080 0.0507 1.0000
6.500 0.7615 0.02292 0.01300 -0.0070 0.0447 1.0000
6.750 0.7807 0.02446 0.01456 -0.0058 0.0416 1.0000
7.000 0.8028 0.02593 0.01623 -0.0048 0.0391 1.0000
7.250 0.8249 0.02739 0.01791 -0.0039 0.0357 1.0000
7.500 0.8453 0.02877 0.01934 -0.0032 0.0323 1.0000
7.750 0.8661 0.03131 0.02209 -0.0023 0.0305 1.0000
8.000 0.8866 0.03367 0.02488 -0.0012 0.0292 1.0000
8.250 0.9045 0.03599 0.02765 0.0001 0.0268 1.0000
8.500 0.9203 0.03805 0.03004 0.0013 0.0245 1.0000
8.750 0.9333 0.04076 0.03310 0.0027 0.0234 1.0000
9.000 0.9431 0.04372 0.03641 0.0041 0.0226 1.0000
9.250 0.9490 0.04705 0.04013 0.0057 0.0221 1.0000
9.500 0.9498 0.05090 0.04432 0.0074 0.0217 1.0000
9.750 0.9445 0.05518 0.04894 0.0091 0.0213 1.0000
10.000 0.9339 0.05940 0.05345 0.0107 0.0211 1.0000
10.250 0.9193 0.06298 0.05731 0.0125 0.0210 1.0000
10.500 0.9024 0.06702 0.06157 0.0130 0.0210 1.0000
10.750 0.8845 0.07174 0.06647 0.0118 0.0210 1.0000
11.000 0.8666 0.07726 0.07213 0.0092 0.0211 1.0000
11.250 0.7124 0.08040 0.07574 0.0106 0.0241 1.0000
11.500 0.6763 0.09305 0.08842 0.0036 0.0253 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GIII BL207 AIRFOIL (giiih-il)