GIII BL332 AIRFOIL (giiij-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GIII BL332 AIRFOIL (giiij-il) Reynolds number: 100,000 Max Cl/Cd: 43.07 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiij-il-100000-n5.txt Download as CSV file: xf-giiij-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL332 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
------ -------- --------- --------- -------- -------- --------
-8.500 -0.5590 0.08807 0.08307 -0.0125 1.0000 0.0557
-8.250 -0.5627 0.08320 0.07823 -0.0171 1.0000 0.0562
-8.000 -0.5646 0.07861 0.07361 -0.0204 1.0000 0.0567
-7.750 -0.5641 0.07409 0.06903 -0.0233 1.0000 0.0576
-7.500 -0.5738 0.07097 0.06529 -0.0280 1.0000 0.0614
-7.250 -0.5655 0.06499 0.05943 -0.0281 1.0000 0.0626
-7.000 -0.5527 0.06171 0.05627 -0.0273 1.0000 0.0648
-6.500 -0.5315 0.04968 0.04311 -0.0263 1.0000 0.0369
-6.250 -0.5204 0.04593 0.03923 -0.0254 1.0000 0.0361
-6.000 -0.5079 0.04274 0.03583 -0.0242 1.0000 0.0357
-5.750 -0.4945 0.03978 0.03261 -0.0227 1.0000 0.0353
-5.500 -0.4800 0.03703 0.02957 -0.0210 1.0000 0.0351
-5.250 -0.4644 0.03450 0.02672 -0.0194 1.0000 0.0350
-5.000 -0.4477 0.03222 0.02410 -0.0176 1.0000 0.0353
-4.750 -0.4295 0.03052 0.02196 -0.0158 1.0000 0.0365
-4.500 -0.4116 0.02857 0.01966 -0.0142 1.0000 0.0377
-4.250 -0.3927 0.02662 0.01752 -0.0129 1.0000 0.0384
-4.000 -0.3725 0.02504 0.01573 -0.0116 1.0000 0.0390
-3.750 -0.3516 0.02367 0.01420 -0.0104 1.0000 0.0397
-3.500 -0.3302 0.02249 0.01286 -0.0093 1.0000 0.0409
-3.250 -0.3088 0.02160 0.01188 -0.0083 1.0000 0.0435
-3.000 -0.2781 0.02062 0.01073 -0.0089 0.9969 0.0463
-2.750 -0.2422 0.01957 0.00955 -0.0105 0.9918 0.0480
-2.500 -0.2060 0.01842 0.00844 -0.0124 0.9861 0.0517
-2.250 -0.1693 0.01760 0.00767 -0.0144 0.9783 0.0559
-2.000 -0.1323 0.01689 0.00692 -0.0164 0.9702 0.0591
-1.750 -0.0945 0.01625 0.00626 -0.0186 0.9632 0.0654
-1.500 -0.0610 0.01582 0.00579 -0.0198 0.9546 0.0721
-1.250 -0.0251 0.01537 0.00534 -0.0215 0.9479 0.0823
-1.000 0.0034 0.01412 0.00496 -0.0223 0.9388 0.2753
-0.750 0.0226 0.01242 0.00545 -0.0182 0.9342 0.8699
-0.500 0.0799 0.01254 0.00555 -0.0225 0.9324 0.9557
-0.250 0.1672 0.01248 0.00534 -0.0343 0.9361 1.0000
0.000 0.1994 0.01240 0.00518 -0.0353 0.9218 1.0000
0.250 0.2295 0.01234 0.00505 -0.0359 0.9067 1.0000
0.500 0.2574 0.01229 0.00494 -0.0359 0.8912 1.0000
0.750 0.2837 0.01225 0.00486 -0.0355 0.8756 1.0000
1.000 0.3091 0.01223 0.00480 -0.0349 0.8595 1.0000
1.250 0.3328 0.01223 0.00476 -0.0339 0.8415 1.0000
1.500 0.3559 0.01223 0.00473 -0.0328 0.8222 1.0000
1.750 0.3794 0.01224 0.00472 -0.0316 0.8028 1.0000
2.000 0.4031 0.01225 0.00470 -0.0304 0.7835 1.0000
2.250 0.4260 0.01230 0.00472 -0.0292 0.7611 1.0000
2.500 0.4493 0.01234 0.00472 -0.0279 0.7375 1.0000
2.750 0.4721 0.01242 0.00476 -0.0265 0.7104 1.0000
3.000 0.4947 0.01252 0.00479 -0.0251 0.6789 1.0000
3.250 0.5166 0.01265 0.00482 -0.0235 0.6374 1.0000
3.500 0.5383 0.01286 0.00486 -0.0219 0.5883 1.0000
3.750 0.5598 0.01315 0.00495 -0.0204 0.5367 1.0000
4.000 0.5812 0.01354 0.00511 -0.0189 0.4864 1.0000
4.250 0.6025 0.01399 0.00536 -0.0176 0.4345 1.0000
4.500 0.6234 0.01451 0.00568 -0.0164 0.3725 1.0000
4.750 0.6431 0.01520 0.00604 -0.0151 0.3026 1.0000
5.000 0.6627 0.01603 0.00651 -0.0140 0.2340 1.0000
5.250 0.6825 0.01692 0.00709 -0.0129 0.1760 1.0000
5.500 0.7030 0.01779 0.00774 -0.0120 0.1386 1.0000
5.750 0.7236 0.01865 0.00847 -0.0110 0.1153 1.0000
6.000 0.7446 0.01947 0.00925 -0.0101 0.1003 1.0000
6.250 0.7650 0.02036 0.01010 -0.0091 0.0888 1.0000
6.500 0.7865 0.02114 0.01095 -0.0082 0.0792 1.0000
6.750 0.8066 0.02214 0.01198 -0.0071 0.0727 1.0000
7.000 0.8277 0.02302 0.01293 -0.0062 0.0661 1.0000
7.250 0.8477 0.02414 0.01405 -0.0053 0.0613 1.0000
7.500 0.8690 0.02524 0.01529 -0.0043 0.0573 1.0000
7.750 0.8898 0.02632 0.01644 -0.0035 0.0536 1.0000
8.000 0.9100 0.02768 0.01783 -0.0027 0.0503 1.0000
8.250 0.9315 0.02904 0.01943 -0.0018 0.0475 1.0000
8.500 0.9523 0.03058 0.02115 -0.0010 0.0453 1.0000
8.750 0.9723 0.03209 0.02283 -0.0002 0.0433 1.0000
9.000 0.9910 0.03371 0.02448 0.0005 0.0414 1.0000
9.250 1.0083 0.03573 0.02682 0.0016 0.0395 1.0000
9.500 1.0239 0.03802 0.02951 0.0028 0.0381 1.0000
9.750 1.0367 0.04060 0.03248 0.0041 0.0369 1.0000
10.000 1.0466 0.04335 0.03559 0.0056 0.0360 1.0000
10.250 1.0539 0.04600 0.03859 0.0070 0.0350 1.0000
10.500 1.0600 0.04834 0.04118 0.0084 0.0339 1.0000
10.750 1.0657 0.05045 0.04344 0.0097 0.0330 1.0000
11.000 1.0679 0.05309 0.04619 0.0109 0.0321 1.0000
11.250 1.0559 0.05653 0.04994 0.0130 0.0318 1.0000
11.500 1.0382 0.06036 0.05409 0.0145 0.0316 1.0000
11.750 1.0183 0.06485 0.05885 0.0144 0.0315 1.0000
12.000 0.9967 0.07020 0.06442 0.0126 0.0315 1.0000
12.250 0.9734 0.07664 0.07106 0.0090 0.0316 1.0000
12.500 0.9489 0.08445 0.07903 0.0036 0.0318 1.0000
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Polar data table (+)
Polar graphs
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