GIII BL75 AIRFOIL (giiic-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: GIII BL75 AIRFOIL (giiic-il) Reynolds number: 100,000 Max Cl/Cd: 42.42 at α=4.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-giiic-il-100000-n5.txt Download as CSV file: xf-giiic-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL75 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
------ -------- --------- --------- -------- -------- --------
-9.750 -0.6386 0.08654 0.08188 -0.0110 1.0000 0.0253
-9.500 -0.6518 0.07815 0.07350 -0.0183 1.0000 0.0248
-9.250 -0.6688 0.07134 0.06663 -0.0223 1.0000 0.0244
-9.000 -0.6864 0.06575 0.06092 -0.0233 1.0000 0.0240
-8.750 -0.6994 0.06016 0.05513 -0.0233 1.0000 0.0238
-8.500 -0.7081 0.05479 0.04946 -0.0225 1.0000 0.0236
-8.250 -0.7120 0.04980 0.04411 -0.0212 1.0000 0.0236
-8.000 -0.7110 0.04528 0.03916 -0.0194 1.0000 0.0238
-7.750 -0.7055 0.04125 0.03467 -0.0176 1.0000 0.0241
-7.500 -0.6960 0.03767 0.03061 -0.0157 1.0000 0.0247
-7.250 -0.6827 0.03470 0.02718 -0.0139 1.0000 0.0259
-7.000 -0.6665 0.03232 0.02429 -0.0122 1.0000 0.0280
-6.750 -0.6479 0.03023 0.02171 -0.0106 1.0000 0.0293
-6.500 -0.6293 0.02754 0.01872 -0.0093 1.0000 0.0305
-6.250 -0.6094 0.02579 0.01684 -0.0082 1.0000 0.0321
-6.000 -0.5893 0.02451 0.01544 -0.0070 1.0000 0.0346
-5.750 -0.5693 0.02344 0.01418 -0.0056 1.0000 0.0383
-5.500 -0.5497 0.02231 0.01286 -0.0040 1.0000 0.0405
-5.250 -0.5339 0.02099 0.01157 -0.0021 1.0000 0.0435
-5.000 -0.5181 0.02015 0.01069 -0.0001 1.0000 0.0473
-4.750 -0.5023 0.01946 0.00987 0.0019 1.0000 0.0536
-4.500 -0.4781 0.01863 0.00904 0.0021 0.9961 0.0636
-4.250 -0.4451 0.01772 0.00820 0.0005 0.9884 0.0823
-4.000 -0.4122 0.01692 0.00753 -0.0010 0.9806 0.1166
-3.750 -0.3787 0.01616 0.00698 -0.0027 0.9737 0.1709
-3.500 -0.3474 0.01539 0.00652 -0.0040 0.9656 0.2433
-3.250 -0.3215 0.01418 0.00604 -0.0045 0.9572 0.3941
-3.000 -0.2978 0.01310 0.00626 -0.0028 0.9508 0.6885
-2.750 -0.2658 0.01320 0.00648 -0.0023 0.9440 0.7820
-2.500 -0.2312 0.01338 0.00658 -0.0027 0.9376 0.8273
-2.250 -0.1969 0.01356 0.00663 -0.0032 0.9304 0.8564
-2.000 -0.1622 0.01372 0.00666 -0.0039 0.9235 0.8798
-1.750 -0.1229 0.01394 0.00673 -0.0055 0.9172 0.8989
-1.500 -0.0818 0.01422 0.00689 -0.0072 0.9112 0.9222
-1.250 -0.0265 0.01443 0.00697 -0.0120 0.9078 0.9397
-1.000 0.0090 0.01441 0.00685 -0.0136 0.8987 0.9484
-0.750 0.0456 0.01433 0.00668 -0.0155 0.8904 0.9529
-0.500 0.0800 0.01427 0.00653 -0.0171 0.8810 0.9582
-0.250 0.1115 0.01423 0.00644 -0.0180 0.8711 0.9644
0.000 0.1464 0.01416 0.00632 -0.0196 0.8621 0.9692
0.250 0.1777 0.01413 0.00625 -0.0205 0.8522 0.9754
0.500 0.2126 0.01407 0.00618 -0.0222 0.8420 0.9801
0.750 0.2443 0.01402 0.00611 -0.0231 0.8301 0.9859
1.000 0.2771 0.01390 0.00598 -0.0241 0.8142 0.9907
1.250 0.3085 0.01377 0.00583 -0.0247 0.7961 0.9960
1.500 0.3386 0.01365 0.00568 -0.0251 0.7777 1.0000
1.750 0.3606 0.01359 0.00565 -0.0240 0.7595 1.0000
2.000 0.3830 0.01355 0.00562 -0.0230 0.7427 1.0000
2.250 0.4056 0.01352 0.00560 -0.0220 0.7263 1.0000
2.500 0.4281 0.01349 0.00559 -0.0209 0.7093 1.0000
2.750 0.4506 0.01349 0.00564 -0.0199 0.6906 1.0000
3.000 0.4731 0.01350 0.00568 -0.0188 0.6706 1.0000
3.250 0.4954 0.01353 0.00571 -0.0176 0.6490 1.0000
3.500 0.5176 0.01359 0.00578 -0.0164 0.6247 1.0000
3.750 0.5396 0.01368 0.00590 -0.0152 0.5967 1.0000
4.000 0.5613 0.01383 0.00600 -0.0138 0.5655 1.0000
4.250 0.5827 0.01403 0.00616 -0.0125 0.5278 1.0000
4.500 0.6034 0.01430 0.00636 -0.0111 0.4830 1.0000
4.750 0.6232 0.01469 0.00660 -0.0096 0.4285 1.0000
5.000 0.6421 0.01521 0.00694 -0.0081 0.3742 1.0000
5.250 0.6604 0.01584 0.00736 -0.0066 0.3288 1.0000
5.500 0.6782 0.01654 0.00786 -0.0051 0.2884 1.0000
5.750 0.6961 0.01722 0.00839 -0.0037 0.2497 1.0000
6.000 0.7148 0.01782 0.00891 -0.0024 0.2163 1.0000
6.250 0.7330 0.01846 0.00946 -0.0010 0.1818 1.0000
6.500 0.7509 0.01917 0.01009 0.0004 0.1377 1.0000
6.750 0.7661 0.02027 0.01086 0.0020 0.0849 1.0000
7.000 0.7804 0.02158 0.01194 0.0039 0.0582 1.0000
7.250 0.7952 0.02285 0.01319 0.0057 0.0476 1.0000
7.500 0.8111 0.02399 0.01448 0.0075 0.0415 1.0000
7.750 0.8245 0.02540 0.01592 0.0094 0.0367 1.0000
8.000 0.8408 0.02654 0.01724 0.0110 0.0328 1.0000
8.250 0.8558 0.02793 0.01880 0.0127 0.0304 1.0000
8.500 0.8700 0.02951 0.02045 0.0143 0.0285 1.0000
8.750 0.8839 0.03160 0.02261 0.0158 0.0266 1.0000
9.000 0.9009 0.03305 0.02434 0.0172 0.0245 1.0000
9.250 0.9164 0.03490 0.02643 0.0185 0.0229 1.0000
9.500 0.9305 0.03707 0.02886 0.0200 0.0219 1.0000
9.750 0.9424 0.03941 0.03146 0.0215 0.0211 1.0000
10.000 0.9514 0.04190 0.03422 0.0230 0.0205 1.0000
10.250 0.9571 0.04452 0.03711 0.0247 0.0200 1.0000
10.500 0.9593 0.04716 0.03997 0.0264 0.0194 1.0000
10.750 0.9559 0.05010 0.04315 0.0283 0.0188 1.0000
11.250 0.9335 0.05710 0.05063 0.0311 0.0182 1.0000
11.500 0.9199 0.06077 0.05458 0.0312 0.0181 1.0000
11.750 0.9046 0.06511 0.05917 0.0302 0.0180 1.0000
12.000 0.8879 0.07017 0.06445 0.0281 0.0180 1.0000
12.250 0.8701 0.07604 0.07050 0.0249 0.0181 1.0000
12.500 0.8517 0.08274 0.07730 0.0207 0.0182 1.0000
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Polar data table (+)
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