HQ 1.0/12 AIRFOIL (hq1012-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HQ 1.0/12 AIRFOIL (hq1012-il) Reynolds number: 50,000 Max Cl/Cd: 31.96 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-hq1012-il-50000-n5.txt Download as CSV file: xf-hq1012-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HQ 1.0/12 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.5962 0.09804 0.09087 -0.0280 1.0000 0.0537
-11.250 -0.6121 0.08973 0.08264 -0.0332 1.0000 0.0534
-11.000 -0.6328 0.08176 0.07466 -0.0386 1.0000 0.0530
-10.750 -0.6558 0.07482 0.06769 -0.0431 1.0000 0.0525
-10.500 -0.6789 0.06914 0.06191 -0.0462 1.0000 0.0521
-10.250 -0.7013 0.06447 0.05712 -0.0474 1.0000 0.0519
-10.000 -0.7216 0.06063 0.05311 -0.0466 1.0000 0.0520
-9.750 -0.7362 0.05672 0.04893 -0.0455 1.0000 0.0524
-9.500 -0.7459 0.05287 0.04469 -0.0441 1.0000 0.0533
-9.250 -0.7516 0.04927 0.04055 -0.0423 1.0000 0.0549
-9.000 -0.7413 0.04708 0.03843 -0.0413 1.0000 0.0580
-8.750 -0.7327 0.04479 0.03594 -0.0399 1.0000 0.0613
-8.500 -0.7240 0.04194 0.03263 -0.0383 1.0000 0.0647
-8.250 -0.7128 0.03943 0.02974 -0.0367 1.0000 0.0689
-8.000 -0.6981 0.03778 0.02807 -0.0354 1.0000 0.0742
-7.750 -0.6825 0.03572 0.02558 -0.0338 1.0000 0.0799
-7.500 -0.6665 0.03419 0.02410 -0.0325 1.0000 0.0863
-7.250 -0.6488 0.03261 0.02220 -0.0309 1.0000 0.0935
-7.000 -0.6322 0.03129 0.02097 -0.0294 1.0000 0.1012
-6.750 -0.6145 0.03002 0.01951 -0.0277 1.0000 0.1098
-6.500 -0.5977 0.02886 0.01834 -0.0259 1.0000 0.1177
-6.250 -0.5831 0.02784 0.01733 -0.0240 1.0000 0.1284
-6.000 -0.5696 0.02691 0.01639 -0.0219 1.0000 0.1410
-5.750 -0.5568 0.02598 0.01549 -0.0197 1.0000 0.1546
-5.500 -0.5451 0.02511 0.01469 -0.0175 1.0000 0.1739
-5.250 -0.5337 0.02421 0.01391 -0.0154 1.0000 0.1991
-5.000 -0.5220 0.02329 0.01311 -0.0133 1.0000 0.2330
-4.750 -0.5102 0.02232 0.01241 -0.0114 1.0000 0.2816
-4.500 -0.4985 0.02141 0.01195 -0.0094 1.0000 0.3481
-4.250 -0.4872 0.02086 0.01185 -0.0068 1.0000 0.4322
-4.000 -0.4667 0.02076 0.01206 -0.0052 0.9958 0.5194
-3.750 -0.4372 0.02099 0.01231 -0.0052 0.9871 0.5902
-3.500 -0.4079 0.02134 0.01260 -0.0048 0.9787 0.6411
-3.250 -0.3775 0.02172 0.01289 -0.0046 0.9709 0.6820
-3.000 -0.3501 0.02199 0.01305 -0.0039 0.9622 0.7129
-2.750 -0.3185 0.02221 0.01309 -0.0042 0.9550 0.7390
-2.500 -0.2898 0.02233 0.01308 -0.0040 0.9466 0.7595
-2.250 -0.2584 0.02243 0.01303 -0.0045 0.9392 0.7798
-2.000 -0.2285 0.02253 0.01301 -0.0045 0.9314 0.7995
-1.750 -0.1969 0.02267 0.01305 -0.0047 0.9243 0.8212
-1.500 -0.1650 0.02276 0.01305 -0.0051 0.9169 0.8419
-1.250 -0.1276 0.02281 0.01299 -0.0068 0.9104 0.8575
-1.000 -0.0922 0.02281 0.01290 -0.0085 0.9028 0.8704
-0.750 -0.0498 0.02284 0.01282 -0.0115 0.8968 0.8819
-0.500 -0.0118 0.02287 0.01279 -0.0137 0.8889 0.8932
-0.250 0.0332 0.02289 0.01274 -0.0172 0.8829 0.9036
0.000 0.0711 0.02292 0.01274 -0.0195 0.8742 0.9149
0.250 0.1178 0.02293 0.01272 -0.0234 0.8677 0.9244
0.500 0.1604 0.02296 0.01275 -0.0266 0.8591 0.9343
0.750 0.2042 0.02297 0.01275 -0.0300 0.8513 0.9443
1.000 0.2498 0.02296 0.01276 -0.0338 0.8429 0.9535
1.250 0.2933 0.02297 0.01282 -0.0373 0.8333 0.9630
1.500 0.3387 0.02285 0.01275 -0.0408 0.8241 0.9724
1.750 0.3823 0.02261 0.01258 -0.0436 0.8108 0.9820
2.000 0.4218 0.02235 0.01237 -0.0457 0.7933 0.9930
2.250 0.4505 0.02215 0.01222 -0.0458 0.7758 1.0000
2.500 0.4648 0.02211 0.01223 -0.0435 0.7602 1.0000
2.750 0.4788 0.02212 0.01228 -0.0411 0.7456 1.0000
3.000 0.4934 0.02215 0.01234 -0.0388 0.7308 1.0000
3.250 0.5092 0.02218 0.01241 -0.0365 0.7156 1.0000
3.500 0.5265 0.02221 0.01248 -0.0345 0.6998 1.0000
3.750 0.5458 0.02221 0.01255 -0.0326 0.6832 1.0000
4.000 0.5671 0.02217 0.01256 -0.0310 0.6658 1.0000
4.250 0.5880 0.02217 0.01261 -0.0293 0.6464 1.0000
4.500 0.6083 0.02220 0.01274 -0.0275 0.6240 1.0000
4.750 0.6296 0.02220 0.01280 -0.0258 0.5997 1.0000
5.000 0.6513 0.02218 0.01282 -0.0241 0.5721 1.0000
5.250 0.6725 0.02223 0.01288 -0.0223 0.5402 1.0000
5.500 0.6941 0.02230 0.01293 -0.0206 0.5048 1.0000
5.750 0.7143 0.02256 0.01308 -0.0188 0.4663 1.0000
6.000 0.7339 0.02296 0.01332 -0.0170 0.4282 1.0000
6.250 0.7521 0.02356 0.01378 -0.0153 0.3912 1.0000
6.500 0.7695 0.02429 0.01434 -0.0137 0.3575 1.0000
6.750 0.7863 0.02511 0.01506 -0.0121 0.3262 1.0000
7.000 0.8026 0.02601 0.01584 -0.0105 0.2981 1.0000
7.250 0.8188 0.02699 0.01675 -0.0091 0.2716 1.0000
7.500 0.8351 0.02803 0.01777 -0.0077 0.2470 1.0000
7.750 0.8513 0.02913 0.01879 -0.0064 0.2251 1.0000
8.000 0.8673 0.03024 0.01998 -0.0050 0.2029 1.0000
8.250 0.8821 0.03138 0.02114 -0.0036 0.1838 1.0000
8.500 0.8979 0.03259 0.02236 -0.0023 0.1669 1.0000
8.750 0.9130 0.03385 0.02367 -0.0010 0.1513 1.0000
9.000 0.9287 0.03520 0.02503 0.0002 0.1385 1.0000
9.250 0.9444 0.03661 0.02647 0.0013 0.1274 1.0000
9.500 0.9591 0.03814 0.02815 0.0025 0.1163 1.0000
9.750 0.9755 0.03989 0.03009 0.0036 0.1074 1.0000
10.000 0.9898 0.04153 0.03165 0.0047 0.0996 1.0000
10.250 0.9986 0.04346 0.03393 0.0063 0.0917 1.0000
10.500 1.0105 0.04534 0.03579 0.0075 0.0857 1.0000
10.750 1.0147 0.04764 0.03847 0.0093 0.0797 1.0000
11.000 1.0227 0.04954 0.04034 0.0105 0.0748 1.0000
11.250 1.0242 0.05251 0.04365 0.0119 0.0711 1.0000
11.500 1.0201 0.05552 0.04699 0.0133 0.0675 1.0000
11.750 1.0183 0.05810 0.04968 0.0141 0.0641 1.0000
12.000 1.0212 0.06078 0.05234 0.0147 0.0611 1.0000
12.250 1.0066 0.06515 0.05709 0.0148 0.0601 1.0000
12.500 0.9881 0.07015 0.06241 0.0141 0.0593 1.0000
12.750 0.9670 0.07583 0.06837 0.0123 0.0589 1.0000
13.000 0.9428 0.08250 0.07526 0.0093 0.0589 1.0000
13.250 0.9160 0.09037 0.08330 0.0049 0.0593 1.0000
13.500 0.8862 0.09985 0.09292 -0.0009 0.0599 1.0000
13.750 0.8565 0.11070 0.10383 -0.0076 0.0606 1.0000
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