GIII BL45 AIRFOIL (giiib-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GIII BL45 AIRFOIL (giiib-il) Reynolds number: 500,000 Max Cl/Cd: 68.53 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-giiib-il-500000.txt Download as CSV file: xf-giiib-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GIII BL45 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4758 0.13448 0.13232 0.0021 1.0000 0.0204
-12.750 -0.4784 0.13064 0.12848 0.0005 1.0000 0.0214
-12.500 -0.6307 0.13664 0.13436 0.0159 1.0000 0.0183
-12.250 -0.6276 0.13283 0.13056 0.0145 1.0000 0.0188
-9.750 -0.8527 0.04143 0.03797 -0.0215 1.0000 0.0124
-9.500 -0.8572 0.03752 0.03371 -0.0187 1.0000 0.0124
-9.250 -0.8578 0.03381 0.02967 -0.0160 1.0000 0.0126
-9.000 -0.8441 0.03250 0.02826 -0.0147 1.0000 0.0132
-8.750 -0.8251 0.03207 0.02784 -0.0140 1.0000 0.0138
-8.500 -0.8171 0.02894 0.02434 -0.0114 1.0000 0.0140
-8.250 -0.8065 0.02602 0.02104 -0.0088 1.0000 0.0142
-8.000 -0.7916 0.02394 0.01867 -0.0068 1.0000 0.0145
-7.750 -0.7751 0.02224 0.01674 -0.0049 1.0000 0.0150
-7.500 -0.7577 0.02083 0.01513 -0.0030 1.0000 0.0155
-7.250 -0.7399 0.01969 0.01382 -0.0011 1.0000 0.0161
-7.000 -0.7222 0.01888 0.01286 0.0008 1.0000 0.0165
-6.750 -0.7091 0.01713 0.01095 0.0034 1.0000 0.0175
-6.500 -0.6967 0.01636 0.01016 0.0060 1.0000 0.0186
-6.250 -0.6659 0.01565 0.00940 0.0050 0.9976 0.0199
-6.000 -0.6306 0.01481 0.00849 0.0032 0.9946 0.0214
-5.750 -0.5963 0.01417 0.00776 0.0017 0.9907 0.0227
-5.500 -0.5647 0.01299 0.00650 0.0005 0.9864 0.0255
-5.250 -0.5288 0.01245 0.00596 -0.0015 0.9836 0.0287
-5.000 -0.4954 0.01198 0.00542 -0.0028 0.9787 0.0316
-4.750 -0.4637 0.01126 0.00470 -0.0038 0.9731 0.0395
-4.500 -0.4304 0.01073 0.00419 -0.0051 0.9683 0.0522
-4.250 -0.4026 0.01020 0.00378 -0.0053 0.9597 0.0776
-4.000 -0.3738 0.00971 0.00349 -0.0057 0.9525 0.1211
-3.750 -0.3478 0.00933 0.00325 -0.0054 0.9432 0.1627
-3.500 -0.3232 0.00895 0.00303 -0.0049 0.9336 0.2078
-3.250 -0.3002 0.00843 0.00279 -0.0040 0.9244 0.2807
-3.000 -0.2825 0.00759 0.00249 -0.0023 0.9135 0.4206
-2.750 -0.2681 0.00673 0.00230 0.0003 0.9028 0.6029
-2.500 -0.2472 0.00640 0.00222 0.0020 0.8939 0.6827
-2.250 -0.2245 0.00619 0.00217 0.0034 0.8847 0.7371
-2.000 -0.2006 0.00608 0.00217 0.0046 0.8758 0.7808
-1.750 -0.1754 0.00604 0.00215 0.0055 0.8678 0.8123
-1.500 -0.1500 0.00603 0.00218 0.0064 0.8582 0.8376
-1.250 -0.1240 0.00606 0.00218 0.0071 0.8494 0.8563
-1.000 -0.0977 0.00609 0.00219 0.0077 0.8402 0.8715
-0.750 -0.0721 0.00612 0.00218 0.0085 0.8269 0.8850
-0.500 -0.0470 0.00617 0.00216 0.0096 0.8110 0.8980
-0.250 -0.0203 0.00624 0.00220 0.0102 0.7962 0.9095
0.000 0.0070 0.00634 0.00226 0.0108 0.7822 0.9201
0.250 0.0342 0.00647 0.00235 0.0114 0.7671 0.9311
0.500 0.0604 0.00661 0.00244 0.0122 0.7509 0.9418
0.750 0.0938 0.00674 0.00251 0.0112 0.7332 0.9458
1.000 0.1246 0.00682 0.00252 0.0107 0.7146 0.9502
1.250 0.1515 0.00691 0.00252 0.0110 0.6959 0.9560
1.500 0.1864 0.00702 0.00255 0.0095 0.6763 0.9582
1.750 0.2215 0.00713 0.00260 0.0079 0.6566 0.9606
2.250 0.2842 0.00737 0.00269 0.0063 0.6163 0.9686
2.500 0.3189 0.00749 0.00274 0.0047 0.5930 0.9708
2.750 0.3552 0.00762 0.00279 0.0028 0.5680 0.9727
3.000 0.3901 0.00776 0.00286 0.0011 0.5419 0.9750
3.250 0.4231 0.00792 0.00295 -0.0002 0.5124 0.9781
3.500 0.4519 0.00814 0.00305 -0.0006 0.4770 0.9825
3.750 0.4863 0.00844 0.00314 -0.0023 0.4180 0.9843
4.000 0.5195 0.00896 0.00332 -0.0040 0.3321 0.9863
4.250 0.5520 0.00946 0.00356 -0.0056 0.2781 0.9886
4.500 0.5847 0.00981 0.00379 -0.0070 0.2504 0.9913
4.750 0.6164 0.01011 0.00401 -0.0082 0.2283 0.9941
5.000 0.6512 0.01038 0.00419 -0.0101 0.2072 0.9958
5.250 0.6857 0.01060 0.00437 -0.0119 0.1905 0.9978
5.500 0.7201 0.01081 0.00457 -0.0137 0.1771 0.9998
5.750 0.7446 0.01101 0.00476 -0.0133 0.1637 1.0000
6.000 0.7673 0.01121 0.00495 -0.0126 0.1482 1.0000
6.250 0.7888 0.01151 0.00516 -0.0117 0.1214 1.0000
6.500 0.8032 0.01273 0.00588 -0.0099 0.0417 1.0000
6.750 0.8201 0.01354 0.00665 -0.0081 0.0273 1.0000
7.000 0.8388 0.01401 0.00718 -0.0065 0.0235 1.0000
7.250 0.8529 0.01496 0.00820 -0.0042 0.0202 1.0000
7.500 0.8706 0.01542 0.00874 -0.0024 0.0192 1.0000
7.750 0.8869 0.01600 0.00938 -0.0004 0.0179 1.0000
8.000 0.9027 0.01658 0.01001 0.0016 0.0166 1.0000
8.250 0.9155 0.01743 0.01090 0.0040 0.0153 1.0000
8.500 0.9227 0.01882 0.01240 0.0074 0.0144 1.0000
8.750 0.9379 0.01951 0.01318 0.0095 0.0140 1.0000
9.000 0.9520 0.02035 0.01412 0.0117 0.0135 1.0000
9.250 0.9655 0.02131 0.01516 0.0139 0.0130 1.0000
9.500 0.9788 0.02234 0.01628 0.0161 0.0125 1.0000
9.750 0.9923 0.02345 0.01749 0.0181 0.0121 1.0000
10.000 1.0056 0.02466 0.01879 0.0200 0.0117 1.0000
10.250 1.0185 0.02598 0.02022 0.0219 0.0114 1.0000
10.500 1.0303 0.02745 0.02178 0.0237 0.0110 1.0000
10.750 1.0392 0.02961 0.02408 0.0256 0.0106 1.0000
11.250 1.0439 0.03462 0.02957 0.0307 0.0101 1.0000
11.500 1.0452 0.03629 0.03144 0.0332 0.0100 1.0000
11.750 1.0428 0.03861 0.03396 0.0353 0.0099 1.0000
12.000 1.0377 0.04126 0.03683 0.0370 0.0099 1.0000
12.250 1.0299 0.04431 0.04009 0.0381 0.0098 1.0000
12.500 1.0195 0.04785 0.04385 0.0385 0.0098 1.0000
12.750 1.0068 0.05193 0.04813 0.0380 0.0098 1.0000
13.000 0.9921 0.05664 0.05304 0.0366 0.0099 1.0000
13.250 0.9757 0.06207 0.05867 0.0341 0.0099 1.0000
13.500 0.9578 0.06828 0.06505 0.0306 0.0099 1.0000
13.750 0.9379 0.07533 0.07227 0.0263 0.0100 1.0000
14.000 0.9151 0.08350 0.08058 0.0212 0.0101 1.0000
14.500 0.7736 0.08655 0.08378 0.0282 0.0104 1.0000
14.750 0.7565 0.09335 0.09069 0.0247 0.0105 1.0000
15.000 0.7379 0.10065 0.09810 0.0208 0.0106 1.0000
15.250 0.5815 0.13298 0.13082 0.0059 0.0154 1.0000
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